Inflatable cascade assembly, system, and method for a cascade thrust reverser system

There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body.

BACKGROUND

1) Field of the Disclosure

The disclosure relates generally to thrust reverser assemblies, systems, and methods for air vehicle engines, and more particularly, to cascade thrust reverser assemblies, systems, and methods for aircraft gas turbine engines.

2) Description of Related Art

Vehicles, such as commercial and military jet aircraft, use thrust reverser assemblies and systems on the aircraft's jet engines, such as gas turbine engines, to block forward thrust or redirect the forward thrust into a reverse thrust, in order to reduce the aircraft's speed just after landing, to reduce wear on the aircraft's brakes, and to enable shorter landing distances.

One type of thrust reverser assembly or system used on large jet engines on aircraft includes a cascade thrust reverser assembly or system having an engine nacelle with a fixed forward portion, and a translating sleeve aft portion, that when translated in an aft direction, reveals individual cascade assemblies that are fixed in place and made of a solid material, such as composites or metal. There are typically 16 (sixteen) cascade assemblies per jet engine, and each cascade assembly has multiple angled vanes that enable, during a landing operation, redirecting an engine fan forward air flow in reverse and side directions to shape reverse efflux air flow and create reverse thrust to enable aerodynamic breaking.

However, known composite or metal solid cascade thrust reverser assemblies and systems may penalize the engine nacelle package, as the solid composite or metal material making up such known composite or metal solid cascade thrust reverser assemblies and systems may be heavy in weight, which may increase the aerodynamic drag and may increase the weight of the aircraft. Such increased weight of the aircraft, may, in turn, increase the fuel costs to operate the aircraft.

In addition, such known composite or metal solid cascade thrust reverser assemblies and systems may, during a forward thrust mode, e.g., a stowed position, limit hard-point constraints to design a shorter or more compact nacelle package. For example, during an aircraft's nacelle package product development design, thrust reverser cascade placement and positioning within the engine may be limited by its surrounding hard-point constraints, for example, an aft cascade support ring which is typically fixed and not movable or translatable, and external nacelle and fan duct outer wall aerodynamic lines. With such hard-point constraints from the aft cascade support ring and the external nacelle and fan duct outer wall aerodynamic lines, the design of such known composite or metal solid cascade thrust reverser assemblies and systems may be limited to maximize the nacelle performance. This, in turn, may limit fan nozzle performance and efficiency, as well as fan duct efficiency.

Moreover, the shape and the length of the 16 (sixteen) cascade assemblies and the multiple angled vanes of such known composite or metal solid cascade thrust reverser assemblies may limit designing a compact engine nacelle configuration or package. For example, known composite or metal solid cascade thrust reverser assemblies may have a length (forward-aft) of about 20 (twenty) inches long to about 30-35 (thirty to thirty-five) inches long. Such long lengths may limit designing a compact engine nacelle configuration or package, which, in turn, may limit the efficiency and performance of the jet engines.

Accordingly, there is a continuing need for an improved cascade thrust reverser assembly, system, and method for aircraft engines to reduce aerodynamic drag, to increase fan nozzle efficiency, to increase fan duct efficiency, to reduce the weight and the length of the nacelle of the engine, to increase the efficiency and performance of the jet engines, and to provide advantages over known assemblies, systems, and methods.

SUMMARY

This need for an improved cascade thrust reverser assembly, system, and method for aircraft engines is satisfied. As discussed in the below detailed description, examples of the improved cascade thrust reverser assembly, system, and method for aircraft engines may provide significant advantages over existing assemblies, systems and methods.

In a disclosed example, there is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly comprises a plurality of inflatable cascade members configured for inflation with a pressurized fluid. The plurality of inflatable cascade members is movable between a stowed deflated state and a deployed inflated state.

Each inflatable cascade member comprises a forward end, an aft end, and a body formed between the forward end and the aft end. The body comprises a plurality of circumferential vanes that are spaced apart and laterally extending. Each circumferential vane comprises a first non-inflatable rigid side attached adjacent to a second inflatable flexible side.

The body further comprises a plurality of inflatable support members that are spaced apart and longitudinally extending. The plurality of inflatable support members is coupled in a perpendicular arrangement to the plurality of circumferential vanes. The body further comprises a plurality of flow openings defined between the plurality of circumferential vanes and the plurality of inflatable support members.

Each inflatable cascade member further comprises a first extendable side support coupled to first ends side of the body. Each inflatable cascade member further comprises a second extendable side support coupled to second side ends of the body. The first extendable side support and the second extendable side support are positioned parallel to the plurality of inflatable support members.

In another disclosed example, there is provided an inflatable cascade system for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade system comprises an inflatable cascade assembly coupled to a fixed portion of a nacelle of the engine. The inflatable cascade assembly comprises a plurality of inflatable cascade members movable between a stowed deflated state, when the cascade thrust reverser system is in a stowed forward thrust mode, and a deployed inflated state, when the cascade thrust reverser system is in a deployed reverse thrust mode. Each inflatable cascade member comprises a forward end, an aft end, and a body formed between the forward end and the aft end.

The inflatable cascade system further comprises a forward flow valve coupled to the forward end. The inflatable cascade system further comprises a pressurized fluid supply system coupled to the forward flow valve. The pressurized fluid supply system provides pressurized fluid to the plurality of inflatable cascade members, via the forward flow valve, to inflate the plurality of inflatable cascade members.

The inflatable cascade system further comprises a translating aft cascade support ring coupled at the aft end. The inflatable cascade system further comprises an aft flow valve coupled to the aft end.

In another disclosed example, there is provided a method of using an inflatable cascade system for a cascade thrust reverser system in an engine of an air vehicle, to provide a reduced aerodynamic drag of the engine, and to provide an increased fan nozzle efficiency of the engine. The method comprises the step of installing an inflatable cascade system for a cascade thrust reverser system, in the engine of the air vehicle.

The inflatable cascade system comprises an inflatable cascade assembly coupled to a fixed portion of a nacelle of the engine. The inflatable cascade assembly comprises a plurality of inflatable cascade members movable between a stowed deflated state, when the cascade thrust reverser system is in a stowed forward thrust mode, and a deployed inflated state, when the cascade thrust reverser system is in a deployed reverse thrust mode. Each inflatable cascade member comprises a forward end, an aft end, and a body formed between the forward end and the aft end.

The inflatable cascade system further comprises a forward flow valve coupled to the forward end. The inflatable cascade system further comprises a pressurized fluid supply system coupled to the forward flow valve. The pressurized fluid supply system has a pressurized fluid. The inflatable cascade system further comprises a translating aft cascade support ring coupled at the aft end. The inflatable cascade system further comprises an aft flow valve coupled to the aft end. The inflatable cascade system provides the reduced aerodynamic drag of the engine, and provides the increased fan nozzle efficiency of the engine.

The method further comprises the step of, upon landing of the air vehicle, concurrently deploying from the stowed forward thrust mode, the translating aft cascade support ring, and a reduced length translating sleeve and one or more blocker doors, of the cascade thrust reverser system. The method further comprises the step of opening the forward flow valve, and fully inflating the plurality of inflatable cascade members with the pressurized fluid from the pressurized fluid supply system, to form a trapped fluid in the plurality of inflatable cascade members, and to move the plurality of inflatable cascade members from the stowed deflated state to the deployed inflated state.

The method further comprises redirecting a fan air flow with the fully inflated plurality of inflatable cascade members and with the one or more deployed blocker doors, to generate the deployed reverse thrust mode of the cascade thrust reverser system. The method further comprises the step of closing the forward flow valve, and opening the aft flow valve to release the trapped fluid from the fully inflated plurality of inflatable cascade members, out through one or more pressure relief vents in the reduced length translating sleeve, and to move the plurality of inflatable cascade members from the deployed inflated state back to the stowed deflated state. The method further comprises the step of moving concurrently the translating aft cascade support ring, and the reduced length translating sleeve and the one or more blocker doors, from the deployed reverse thrust mode back to the stowed forward thrust mode, and closing the aft flow valve.

The features, functions, and advantages that have been discussed can be achieved independently in various examples of the disclosure or may be combined in yet other examples further details of which can be seen with reference to the following description and drawings.

DETAILED DESCRIPTION

Disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all of the disclosed examples are shown. Indeed, several different examples may be provided and should not be construed as limited to the examples set forth herein. Rather, these examples are provided so that this disclosure will be thorough and complete and will fully convey the scope of the disclosure to those skilled in the art.

Now referring to the Figures,FIG. 1is an illustration of a perspective view of a vehicle11, such as an air vehicle12, for example, an aircraft12a, that may incorporate a disclosed example of an inflatable cascade system10for a cascade thrust reverser system24, such as in the form of an inflatable cascade thrust reverser system24a. As shown inFIG. 1, the vehicle11, such as the air vehicle12, for example, the aircraft12a, comprises two nacelles14which shroud or surround two engines16, respectively, for example, gas turbine engines16a, or turbofan engines. The vehicle11(seeFIG. 1), such as the air vehicle12(seeFIG. 1), for example, the aircraft12a(seeFIG. 1), further comprises wings18(seeFIG. 1), a fuselage20(seeFIG. 1), and a tail22(seeFIG. 1). As shown inFIG. 1, each engine16and nacelle14includes the inflatable cascade system10for the cascade thrust reverser system24, such as in the form of inflatable cascade thrust reverser system24a. As further shown inFIG. 1, the vehicle11, such as the air vehicle12, for example, the aircraft12a, may include a hydraulic fluid system26having hydraulic fluid distribution elements28, such as in the form of ducting, tubing, or other suitable distribution elements, that may be incorporated throughout portions in the wings18and engines16.

As used herein, “cascade thrust reverser system” and “cascade thrust reverser” mean a system configured to reverse or divert an aircraft engine's thrust, so that it is directed in a forward direction60(seeFIG. 9C), rather than in an aft direction62(seeFIG. 9C), and that uses a plurality of cascade members, such as inflatable cascade members82(seeFIGS. 9A-9D) and blocker doors48(seeFIGS. 9A-9D) deployed to block the engine's direct air flow exhaust exit and redirect or deflect an air flow33(seeFIG. 9A) through the plurality of cascade members, such as the inflatable cascade members82(seeFIGS. 9A-9D) so as to create a thrust reversal. The cascade thrust reverser system24(seeFIG. 1) helps to slow down the vehicle11(see FIG.1), such as the air vehicle12(seeFIG. 1), for example, the aircraft12a(seeFIG. 1), upon landing or touchdown or just after landing or touchdown, helps to reduce wear on the brakes of the vehicle11(seeFIG. 1), such as the air vehicle12(seeFIG. 1), for example, the aircraft12a(seeFIG. 1), and helps to enable shorter landing distances for the air vehicle12(seeFIG. 1), such as the aircraft12a(seeFIG. 1). As used herein, “landing distance” means a ground roll of the vehicle11(seeFIG. 1), such as the air vehicle12(seeFIG. 1), for example, the aircraft12a(seeFIG. 7), from the point of landing or touchdown to a complete stop or rest.

Now referring toFIG. 2,FIG. 2is an illustration of a top sectional view of a known engine17with a known cascade-type thrust reverser system30having a thrust reverser31shown in a deployed reverse thrust position32. As shown inFIG. 2, air flow33, such as in the form of intake air flow33a, flows into the engine17, which is shrouded by a known nacelle15. The air flow33(seeFIG. 2) flows in at an air flow inlet35(seeFIG. 2) of a fixed portion34(seeFIG. 2) of the nacelle15(seeFIG. 2), such as in the form of an inlet cowl34a(seeFIG. 2). The intake air flow33a(seeFIG. 2) flows through a fan36(seeFIG. 2) and becomes fan air flow33b(seeFIG. 2). The fan36(seeFIG. 2) is disposed within a fan duct37(seeFIG. 2) of the engine17(seeFIG. 2), and the fan duct37terminates in a fan nozzle39(seeFIG. 2). The fan duct37(seeFIG. 2) includes a fan duct inner wall37a(seeFIG. 2) and a fan duct outer wall37b(seeFIG. 2). As shown inFIG. 2, in the deployed reverse thrust position32, the fan air flow33bflows through the fan duct37, around the sides of an engine core38, and around a thrust reverser bullnose fairing40, and is blocked by blocker doors48that are deployed.

As further shown inFIG. 2, the fan air flow33bflows through a known cascade assembly42coupled to an aft cascade support ring44, and exits the nacelle15, as reverse efflux air flow33c, at an opening exit49of the engine17. The known cascade assembly42shown inFIG. 2is made of a solid material, for example, a metal, a composite, or a combination of a metal and a composite, and is manufactured using known processes, such as composite hand lay-up, thermoplastic molding, casting, three-dimensional printing, machining, or another suitable manufacturing process. In addition, the known cascade assembly42, as well as the aft cascade support ring44, shown inFIG. 2, are both fixed in position and do not move or translate, regardless of whether the thrust reverser31is stowed or deployed.

During thrust reversal, instead of being ejected from the rear of the engine17(seeFIG. 2), for example, at the fan nozzle39(seeFIG. 2) or at a core nozzle54(seeFIG. 2), to generate forward thrust, the fan air flow30b(seeFIG. 2) is blocked by blocker doors48(seeFIG. 2) inside the engine17(seeFIG. 2) and directed as reverse efflux air flow30coutside the nacelle15(seeFIG. 2), in a generally forward direction60(seeFIG. 2) to generate a reverse thrust.

The nacelle15(seeFIG. 2) includes the fixed portion34(seeFIG. 2), such as in the form of inlet cowl34a(seeFIG. 2), at a forward end56(seeFIG. 2) of the nacelle15(seeFIG. 2), and the nacelle15(seeFIG. 2) further includes a translating portion50(seeFIG. 2), such as in the form of a translating sleeve50a(seeFIG. 2), at an aft end58(seeFIG. 2) of the nacelle15(seeFIG. 2). The translating sleeve50a(seeFIG. 2) may include pressure relief vents52(seeFIG. 2). As shown inFIG. 2, exhaust air flow30eexits from the core nozzle54of the engine17at the aft end58of the nacelle15.

FIG. 2further shows thrust reverser actuators46, such as in the form of hydraulic actuators46a, for actuating the translating sleeve50ain an aft direction62. When the thrust reverser31(seeFIG. 2) is activated, the thrust reverser actuators46(seeFIG. 2) cause the translating sleeve50a(seeFIG. 2) to move in the aft direction62(seeFIG. 2), uncovering the cascade assembly42(seeFIG. 2). A linkage between the translating sleeve50a(seeFIG. 2) and the blocker doors48(seeFIG. 2) moves the blocker doors48into the fan air flow33b(seeFIG. 2) stream, blocking its normal path and diverting it out through the cascade assembly42, which redirects the fan air flow33bin the forward direction60(seeFIG. 2) out of the engine17, as reverse efflux air flow33c(seeFIG. 2), to help slow down the aircraft12a(seeFIG. 1), upon landing or touchdown.

Now referring toFIG. 3A,FIG. 3Ais an illustration of a partial sectional side view of the known engine17with the known cascade-type thrust reverser system30ofFIG. 2, with the thrust reverser31in the deployed reverse thrust position32.FIG. 3Ashows the known cascade-type thrust reverser system30in a deployed reverse thrust mode64.FIG. 3Afurther shows the air flow33, such as the fan air flow33b, flowing through the fan duct37and around the thrust reverser bullnose fairing40, being blocked by the blocker doors48inside the engine17, being directed through the cascade assembly42, which is coupled to the aft cascade support ring44, and being directed as reverse efflux air flow30coutside the engine17and the nacelle15, in a generally forward direction60to generate the reverse thrust.FIG. 3Afurther shows the fan duct inner wall37aand the fan duct outer wall37b.

FIG. 3Afurther shows the fixed portion34of the nacelle15, such as in the form of the inlet cowl34a, and shows the translating portion50of the nacelle15, such as in the form of the translating sleeve50a, with the pressure relief vents52. The translating portion50(seeFIG. 3A) is translated back in the aft direction62(seeFIG. 3A), to uncover the cascade assembly42(seeFIG. 3A).FIG. 3Afurther shows a torque box66coupled to the fixed portion34of the nacelle15.

Now referring toFIG. 3B,FIG. 3Bis an illustration of a front cross-sectional view of the known cascade assembly42ofFIG. 2, coupled to the aft cascade support ring44, andFIG. 3Bshows the UP direction toward the top of the engine and the INBOARD direction toward the inboard side of the engine.FIG. 3Bshows a support assembly68with the cascade assembly42surrounding the exterior of the support assembly68. As shown inFIG. 3B, the cascade assembly42comprises a plurality of 16 (sixteen) cascades42asurrounding the exterior of the support assembly68, which is a typical number of cascades42afor certain aircraft.FIG. 3Bfurther shows 6 (six) thrust reverser actuators46, such as in the form of hydraulic actuators46a, for actuating the translating portion50(seeFIGS. 2, 3A), such as the translating sleeve50a(seeFIGS. 2, 3A), in the aft direction62(seeFIGS. 2, 3A). AlthoughFIG. 3Bshows 6 (six) thrust reverser actuators46, other nacelles may have four (4), eight (8), or another suitable number of thrust reverser actuators46per nacelle.FIG. 3Bfurther shows a translating assembly70with4(four) sliders70a,70b,70c,70d, or rails, over which the translating portion50(seeFIGS. 2, 3A), such as the translating sleeve50a(seeFIGS. 2, 3A) slides, when the translating portion50is actuated by the thrust reverser actuators46.

Now referring toFIG. 3C,FIG. 3Cis an illustration of a partial sectional side view of the known engine17with the known cascade-type thrust reverser system30ofFIG. 3A, with the with the thrust reverser31in a stowed non-reversing position72.FIG. 3Cshows the known cascade-type thrust reverser system30in a stowed forward thrust mode74.FIG. 3Cfurther shows the air flow33, such as the fan air flow33b, flowing through the fan duct37and along the fan duct inner wall37aand the fan duct outer wall37b, to generate a forward thrust. The blocker doors48(seeFIG. 3C) are stowed. The cascade assembly42(seeFIG. 3C), which is coupled to the aft cascade support ring44(seeFIG. 3C), is stowed.

FIG. 3Cfurther shows the fixed portion34of the nacelle15, such as in the form of the inlet cowl34a, and shows the translating portion50of the nacelle15, such as in the form of the translating sleeve50a, with the pressure relief vents52. The translating portion50(seeFIG. 3C) is translated forward from the aft direction62(seeFIG. 3C) to the forward direction60(seeFIG. 3C), to cover the cascade assembly42(seeFIG. 3C).FIG. 3Cfurther shows the thrust reverser bullnose fairing40and the torque box66.

During an aircraft's nacelle package product development design, thrust reverser cascade placement and positioning within the engine may be limited by its surrounding hard-point constraints, for example, the aft cascade support ring44(seeFIG. 3C), the thrust reverser bullnose fairing40(seeFIG. 3C), and the external nacelle15(seeFIG. 3C) and fan duct outer wall37b(seeFIG. 3C) aerodynamic lines.FIG. 3Cshows that the known engine17having the known cascade-type thrust reverser system30may have a first aft cascade support ring hard-point constraint75athat constrains or limits an external nacelle aerodynamic line76, which may, in turn, limit aerodynamic drag benefits.FIG. 3Cfurther shows that the known engine17having the known cascade-type thrust reverser system30may have a second aft cascade support ring hard-point constraint75bthat may constrain or limit a fan duct outer wall aerodynamic line78, which may, in turn, limit fan nozzle performance.

Now referring toFIG. 4, in a disclosed example, an inflatable cascade system10for a cascade thrust reverser (TR) system24of an engine16, such as a gas turbine engine16a, of a vehicle11, such as an air vehicle12, for example, an aircraft12a, is provided.FIG. 4is an illustration of a functional block diagram showing a disclosed example of the vehicle11, such as the air vehicle12, for example, the aircraft12a, having disclosed examples of the inflatable cascade system10with an inflatable cascade assembly80, for the cascade thrust reverser (TR) system24, such as an inflatable cascade thrust reverser (TR) system24a.

As shown inFIG. 4, the inflatable cascade system10comprises an inflatable cascade assembly80coupled to a fixed portion174of a nacelle14of the engine16. The nacelle14(seeFIG. 4) is preferably a shortened nacelle14a(seeFIG. 4) comprising the fixed portion174(seeFIG. 4), such as an inlet cowl174a(seeFIG. 4), and a reduced length translating portion170(seeFIG. 4), such as a reduced length translating sleeve170a(seeFIG. 4).

As shown inFIG. 4, the engine16, such as the gas turbine engine16a, comprises the cascade thrust reverser (TR) system24, such as in the form of inflatable cascade thrust reverser (TR) system24a, which comprises a cascade thrust reverser176, such as in the form of an inflatable cascade thrust reverser176a. The engine16further includes a thrust reverser (TR) bullnose fairing40. The cascade thrust reverser176, such as in the form of an inflatable cascade thrust reverser176ais actuated by a thrust reverser actuator (TR ACT.)177. As shown inFIG. 4, the thrust reverser actuator177may comprise a hydraulic actuator177a, a pneumatic actuator177b, a mechanical actuator177c, an electrical actuator177d, or another suitable actuator for actuating a thrust reverser. The thrust reverser actuator177(seeFIG. 4) is controlled with an actuator (ACT.) controller178, and is powered with power from an actuator (ACT.) power source179.

The actuator controller178(seeFIG. 4) may comprise one of, a hydraulic actuator controller, a pneumatic actuator controller, a mechanical actuator controller, an electrical actuator controller, or another suitable actuator controller. The actuator power source179(seeFIG. 4) may comprise one of, a hydraulic actuator power source, such as hydraulic power or hydraulic fluid; a pneumatic actuator power source, such as high pressure air; a mechanical actuator power source, such as a rack and pinion; an electrical actuator power source, such as a motor; or another suitable actuator power source.

As further shown inFIG. 4, the inflatable cascade assembly80comprises a plurality of inflatable cascade members82movable between a stowed deflated state84, when the cascade thrust reverser system24is in a stowed forward thrust mode181, and a deployed inflated state86, when the cascade thrust reverser system24is in a deployed reverse thrust mode186. As further shown inFIG. 4, each inflatable cascade member82comprises a forward end88a, an aft end88b, a plurality of first side ends116aor side end portions, a plurality of second side ends116bor side end portions, and a body90formed between the forward end88aand the aft end88b, and formed between the first side ends116aand the second side ends116b.

The body90(seeFIG. 4) of each inflatable cascade member82(seeFIG. 4) preferably comprises a plurality of circumferential vanes92(seeFIG. 4) that are spaced apart and laterally extending. Each circumferential vane92(seeFIG. 4) comprises a first non-inflatable rigid side94(seeFIG. 4) formed or adjacent to a second inflatable flexible side96(seeFIG. 4). The second inflatable flexible side96(seeFIG. 4) preferably has a thickness100(seeFIG. 4) that is greater than a thickness98(seeFIG. 4) of the first non-inflatable rigid side94(seeFIG. 4), when the inflatable cascade member82(seeFIG. 4) is in the deployed inflated state86(seeFIG. 4). The thickness100of the second inflatable flexible side96may be five (5) times greater than the thickness98of the first non-inflatable rigid side94, when the inflatable cascade member82(seeFIG. 4) is in the deployed inflated state86(seeFIG. 4). When the inflatable cascade member82(seeFIG. 4) is in the stowed deflated state84(seeFIG. 4), the thickness of the first non-inflatable rigid side94is preferably greater than the thickness of the second inflatable flexible side96. In the stowed deflated state84(seeFIGS. 4, 6B), the material making up the first non-inflatable rigid side94(seeFIG. 6B) may preferably be thicker and more rigid because it is facing a higher pressure area and may be exposed to a higher pressure, and to provide a shape or configuration of each circumferential vane92(seeFIG. 4) to turn or reverse the fan air flow33b(seeFIG. 9A). The material making up the second inflatable flexible side96(seeFIG. 6B) may preferably be thinner because it is facing a lower pressure area and may be exposed to a lower pressure.

The body90(seeFIG. 4) of each inflatable cascade member82(seeFIG. 4) preferably further comprises a plurality of inflatable support members102(seeFIG. 4), such as in the form of inflatable strongbacks102a(seeFIG. 4), that are spaced apart and longitudinally extending. The plurality of inflatable support members102(seeFIGS. 4, 5D) is coupled in a perpendicular arrangement104(seeFIG. 5C) to the plurality of circumferential vanes92(seeFIGS. 4, 5D). The plurality of inflatable support members102, such as in the form of inflatable strongbacks102a, are movable between a stowed deflated position108(seeFIG. 4), when the cascade thrust reverser system24(seeFIG. 4) is in a stowed forward thrust mode181(seeFIG. 4), and a deployed inflated position110(seeFIG. 4), when the cascade thrust reverser system24is in a deployed reverse thrust mode186(seeFIG. 4).

The second inflatable flexible side96(seeFIG. 4) of the plurality of circumferential vanes92(seeFIG. 4), and the plurality of inflatable support members102(seeFIG. 4), are preferably both made of a flexible material112(seeFIG. 4) comprising one of, a para-aramid synthetic fiber, nylon, rubber, polyvinyl chloride, polyethylene, polypropylene, or another suitable flexible material. Preferably, the para-aramid synthetic fiber is KEVLAR para-aramid synthetic fiber obtained from E. I. Du Pont De Nemours and Company of Wilmington, Del. (KEVLAR is a registered trademark of E. I. Du Pont De Nemours and Company of Wilmington, Del.)

The body90(seeFIG. 4) further comprises a plurality of flow openings106(seeFIG. 4). The flow openings106(seeFIG. 4) are defined between the plurality of circumferential vanes92(seeFIG. 4) and the plurality of inflatable support members102(seeFIG. 4).

Each inflatable cascade member82(seeFIG. 4) further comprises extendable side supports118(seeFIG. 4). The extendable side supports118(seeFIG. 4) preferably comprise a first extendable side support118a(seeFIG. 4) coupled to the first side ends116a(seeFIG. 4) of the body90(seeFIG. 4), and a second extendable side support118b(seeFIG. 4) coupled to the second side ends116b(seeFIG. 4) of the body90. The second extendable side support118b(seeFIG. 4) is preferably positioned opposite the first extendable side support118a(seeFIG. 4). The first extendable side support118a(seeFIG. 4) and the second first extendable side support118b(seeFIG. 4) are preferably positioned parallel to the plurality of inflatable support members102(seeFIG. 4).

As shown inFIG. 4, the inflatable cascade assembly80may further comprise a plenum chamber136. The plenum chamber136(seeFIG. 4) is preferably coupled at the forward end88a(seeFIG. 4) of each inflatable cascade member82and of the inflatable cascade assembly80(seeFIG. 4), and coupled aft of the forward flow valve150(seeFIG. 4). The plenum chamber136(seeFIG. 4) distributes the pressurized fluid120(seeFIG. 4) from the pressurized fluid supply system122(seeFIG. 4) uniformly within each inflatable cascade member82(seeFIG. 4). The plenum chamber136(seeFIG. 4) preferably comprises an orifice plate portion138(seeFIG. 4).

As shown inFIG. 4, the inflatable cascade system10further comprises a forward flow valve150. The forward flow valve (seeFIG. 4) is preferably coupled to the forward end88a(seeFIG. 4) of the inflatable cascade member82(seeFIG. 4). The forward flow valve150(seeFIG. 4) preferably comprises an electronic flow control valve150a(seeFIG. 4), or another suitable flow control valve or mechanism.

As shown inFIG. 4, the inflatable cascade system10(seeFIG. 4) further comprises a pressurized fluid supply system122. The pressurized fluid supply system122(seeFIG. 4) is coupled to the forward flow valve150(seeFIG. 4), which is, in turn, coupled to the inflatable cascade assembly80(seeFIG. 4). As shown inFIG. 4, the pressurized fluid supply system122may comprise one of, a pressurized air supply system122a, an engine compressor bleed air supply system122b, a compressed air supply system122c, one or more compressed air bottles122d, a ram air supply system122e, a hydraulic fluid system26, or another suitable pressurized fluid supply system122.

The pressurized fluid supply system122(seeFIG. 4) provides a pressurized fluid120(seeFIG. 4) to the plurality of inflatable cascade members82(seeFIG. 4), via the forward flow valve150(seeFIG. 4), to inflate the plurality of inflatable cascade members82. As shown inFIG. 4, the pressurized fluid120may comprise one of, pressurized air120a, engine compressor bleed air120b, compressed air120c, hydraulic fluid120d, ram air120e, or another suitable pressurized fluid120.

As shown inFIG. 4, the inflatable cascade system10further comprises a translating aft cascade support ring140. The translating aft cascade support ring140(seeFIG. 4) is coupled at the aft end88b(seeFIG. 4) of the inflatable cascade member82(seeFIG. 4). The translating aft cascade support ring140(seeFIG. 4) is configured for coupling to a translating apparatus148(seeFIG. 4). The translating apparatus148(seeFIG. 4), such as in the form of a slider apparatus148a(seeFIG. 4), is configured to move the translating aft cascade support ring140(seeFIG. 4). The translating aft cascade support ring140(seeFIG. 4), in turn, moves the plurality of inflatable cascade members82(seeFIG. 4) between the stowed deflated state84(seeFIG. 4) and the deployed inflated state86(seeFIG. 4), to elongate and shorten the plurality of inflatable cascade members82(seeFIG. 4). As shown inFIG. 4, the translating aft cascade support ring140may have a rectangular configuration140a, a C-shaped configuration140b, a Z-shaped configuration140c, an I-shaped configuration140d, or another suitable configuration or shape.

As shown inFIG. 4, the inflatable cascade system10further comprises an aft flow valve160coupled to the aft end88bof the inflatable cascade member82. The aft flow valve160(seeFIG. 4) preferably comprises an electronic flow control valve160a(seeFIG. 4), or another suitable flow control valve or mechanism. The aft flow valve160(seeFIG. 4) is configured to release any trapped fluid189(seeFIGS. 9C-9D) from the plurality of inflatable cascade members82(seeFIG. 4), after the plurality of inflatable cascade members82have inflated.

As shown inFIG. 4, the inflatable cascade system10may further comprise one or more safety devices190comprising one or more pressure sensors190a, or pressure transducers or pressure transmitters, configured to signal or trigger an electronic signal for one or more of, an air leakage191ain the inflatable cascade system10, a cascade breach191bof one or more of the plurality of inflatable cascade members82, or another safety issue. In addition, during the stowed forward thrust mode181(seeFIG. 4), to eliminate any unwanted inflation191c(see FIG.4), or pressurization, due to a possible issue or problem with the forward flow valve150(seeFIG. 4), the aft flow valve160(seeFIG. 4) may be kept in an open position.

As shown inFIG. 4, the inflatable cascade system10allows for a shortened nacelle14adesign that preferably provides a reduced aerodynamic drag274, for example, a reduced nacelle external drag275. In addition, the inflatable cascade system10allows for a shortened nacelle14adesign having a reduced weight278and a reduced length279. Further, the inflatable cascade system10allows for an engine16with an increased fan duct efficiency276and an increased fan nozzle efficiency277.

Now referring toFIGS. 5A-5C,FIG. 5Ais an illustration of a side view of a disclosed example of an inflatable cascade assembly80in a deployed inflated state86, where the inflatable cascade assembly80is coupled to the translating aft cascade support ring140.FIG. 5Bis an illustration of a close-up side view of the inflatable cascade assembly80shown in circle5B ofFIG. 5A.FIG. 5Cis an illustration of a close-up top view of the inflatable cascade assembly80ofFIG. 5B.

The inflatable cascade assembly80(seeFIGS. 5A-5C) comprises the inflatable cascade member82(seeFIGS. 5A, 5B) having the forward end88a(seeFIG. 5A), the aft end88b(seeFIG. 5A), the body90(seeFIGS. 5A-5C) formed between the forward end88aand the aft end88b, the first side ends116a(seeFIG. 5C) of the body90, and the second side ends116b(seeFIG. 5C) of the body90. The forward end88a(seeFIG. 5A) of the inflatable cascade member82(seeFIGS. 5A, 5C) is configured to receive the pressurized fluid120(seeFIGS. 5A, 5C) via the forward flow valve150(seeFIG. 4).

FIGS. 5A-5Cshow the plurality of circumferential vanes92that are spaced apart and laterally extending, and the plurality of inflatable support members102, such as in the form of inflatable strongbacks102a, that are spaced apart and longitudinally extending. The plurality of inflatable support members102(seeFIGS. 5A-5D) is coupled in a perpendicular arrangement104(seeFIG. 5C) to the plurality of circumferential vanes92(seeFIGS. 5A-5D).FIG. 5Cshows the inflatable support members102in a deployed inflated position110.

Each circumferential vane92(seeFIGS. 5A-5C) comprises the first non-inflatable rigid side94(seeFIGS. 5B, 5C) formed or attached adjacent to the second inflatable flexible side96(seeFIGS. 5B, 5C). As shown inFIG. 5B, the second inflatable flexible side96has an interior97aand an exterior97b. As further shown inFIG. 5B, the second inflatable flexible side96preferably has a thickness100that is greater than a thickness98of the first non-inflatable rigid side94, when the inflatable cascade member82and the inflatable cascade assembly80is in the deployed inflated state86.

As shown inFIG. 5A, the inflatable cascade member82of the inflatable cascade assembly80has a deployed length87. The deployed length87(seeFIG. 5A) is greater than a stowed length85(seeFIG. 6A) of the inflatable cascade member82(seeFIG. 6A) of the inflatable cascade assembly80(seeFIG. 6A).

FIG. 5Afurther shows the translating aft cascade support ring140coupled at the aft end88bof the inflatable cascade member82. As shown inFIG. 5A, in this example, the translating aft cascade support ring140has a rectangular configuration140a. As further shown inFIG. 5A, the translating aft cascade support ring140has a forward end142a, an aft end142b, and a body144formed between the forward end142aand the aft end142b.

FIG. 5Cfurther shows the plurality of flow openings106defined between the plurality of circumferential vanes92and the plurality of inflatable support members102, which plurality of circumferential vanes92and the plurality of inflatable support members102form a basket configuration114. Further,FIG. 5Cshows the extendable side supports118for the inflatable cascade member82of the inflatable cascade assembly80. The extendable side supports118(seeFIG. 5C) preferably comprise a first extendable side support118a(seeFIG. 5C) coupled to the plurality of first side ends116a(seeFIG. 5C) of the body90(seeFIG. 5C), and a second extendable side support118b(seeFIG. 5C) coupled to the plurality of second side ends116b(seeFIG. 5C) of the body90. The second extendable side support118b(seeFIG. 5C) is preferably positioned opposite the first extendable side support118a(seeFIG. 5C). The first extendable side support118a(seeFIG. 5C) and the second first extendable side support118b(seeFIG. 5C) are preferably positioned parallel to the plurality of inflatable support members102(seeFIG. 5C).

Now referring toFIG. 5D,FIG. 5Dis an illustration of a side perspective view of a disclosed example of the inflatable cascade assembly80comprising the inflatable cascade member82, in the deployed inflated state86, having the forward end88a, the aft end88b, the body90formed between the forward end88aand the aft end88b, the first side ends116aof the body90, and the second side ends116bof the body90. As shown inFIG. 5D, the forward end88afaces in a forward direction60, and the aft end88bfaces in an aft direction62.

FIG. 5Dfurther shows the plurality of circumferential vanes92that are spaced apart and laterally extending, and the plurality of inflatable support members102, such as in the form of inflatable strongbacks102a, that are spaced apart and longitudinally extending. The plurality of inflatable support members102(seeFIG. 5D) is coupled in a perpendicular arrangement104(seeFIG. 5D) to the plurality of circumferential vanes92(seeFIG. 5D).

FIG. 5Dfurther shows the plurality of flow openings106defined between the plurality of circumferential vanes92and the plurality of inflatable support members102. Further,FIG. 5Dshows the extendable side supports118for the inflatable cascade member82of the inflatable cascade assembly80. The extendable side supports118(seeFIG. 5D) preferably comprise the first extendable side support118a(seeFIG. 5D) coupled to the plurality of first side ends116a(seeFIG. 5D) of the body90(seeFIG. 5C), and the second extendable side support118b(seeFIG. 5D) coupled to the plurality of second side ends116b(seeFIG. 5D) of the body90. As shown inFIG. 5D, the second extendable side support118bis positioned opposite the first extendable side support118a, and the first extendable side support118aand the second extendable side support118bare positioned parallel to the plurality of inflatable support members102.

Now referring toFIG. 6A,FIG. 6Ais an illustration of a side view of the inflatable cascade assembly80ofFIG. 5Ain a stowed deflated state84, where the inflatable cascade assembly80is coupled to the translating aft cascade support ring140with the rectangular configuration140a.FIG. 6Bis an illustration of a close-up side view of the inflatable cascade assembly80shown in circle6B ofFIG. 6A.FIG. 6Cis an illustration of a close-up top view of the inflatable cascade assembly80ofFIG. 6B.

The inflatable cascade assembly80(seeFIGS. 6A-6C) comprises the inflatable cascade member82(seeFIGS. 6A-6C) having the forward end88a(seeFIG. 6A), the aft end88b(seeFIG. 6A), the body90(seeFIGS. 6A-6C) formed between the forward end88aand the aft end88b, the first side ends116a(seeFIG. 6C) of the body90, and the second side ends116b(seeFIG. 6C) of the body90.FIGS. 6A-6Cshow the plurality of circumferential vanes92that are spaced apart and laterally extending, and the plurality of inflatable support members102, such as in the form of inflatable strongbacks102a, that are spaced apart and longitudinally extending.FIG. 6Cshows the inflatable support members102in a stowed deflated position108.

Each circumferential vane92(seeFIGS. 6A-6C) comprises the first non-inflatable rigid side94(seeFIGS. 6B, 6C) formed or attached adjacent to the second inflatable flexible side96(seeFIGS. 6B, 6C). As shown inFIG. 6A, the inflatable cascade member82of the inflatable cascade assembly80has the stowed length85that is less than the deployed length87(seeFIG. 5A) of the inflatable cascade member82(seeFIG. 5A) of the inflatable cascade assembly80(seeFIG. 5A).

FIG. 6Cfurther shows the plurality of flow openings106defined between the plurality of circumferential vanes92and the plurality of inflatable support members102. Further,FIG. 5Cshows the extendable side supports118for the inflatable cascade member82of the inflatable cascade assembly80. The extendable side supports118(seeFIG. 6C) preferably comprise the first extendable side support118a(seeFIG. 6C) coupled to the plurality of first side ends116a(seeFIG. 6C) of the body90(seeFIG. 6C), and the second extendable side support118b(seeFIG. 6C) coupled to the plurality of second side ends116b(seeFIG. 6C) of the body90.

Now referring toFIG. 7A,FIG. 7Ais an illustration of a close-up side view of another disclosed example of the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, where the second inflatable flexible side96of the one or more of the plurality of circumferential vanes92has a tube configuration128. As shown inFIG. 7A, the tube configuration128comprises a plurality of separate tube elements130.FIG. 7Afurther shows the first non-inflatable rigid side94formed adjacent to or attached to the second inflatable flexible side96having the plurality of separate tube elements130.FIG. 7Afurther shows the plurality of inflatable support members102, such as the form of inflatable strongbacks102a.

Now referring toFIG. 7B,FIG. 7Bis an illustration of a close-up side view of yet another disclosed example of the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, where the second inflatable flexible side96of the one or more of the plurality of circumferential vanes92has a segmented configuration132. As shown inFIG. 7B, the segmented configuration132comprises a plurality of continuous segmented elements134.FIG. 7Bfurther shows the first non-inflatable rigid side94formed adjacent to or attached to the second inflatable flexible side96having the plurality of continuous segmented elements134.FIG. 7Bfurther shows the plurality of inflatable support members102, such as the form of inflatable strongbacks102a.

Now referring toFIG. 8A,FIG. 8Ais an illustration of a side view of a disclosed example of the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, having a plenum chamber136and a forward flow valve150at the forward end88a, and having the translating aft cascade support ring140and an aft flow valve160at the aft end88b. As further shown inFIG. 8A, the inflatable cascade assembly80, comprising the inflatable cascade member82, comprises the body90, the plurality of circumferential vanes92, and the plurality of inflatable support members102, such as the plurality of inflatable strongbacks102a.

Now referring toFIG. 8B,FIG. 8Bis an illustration of a close-up side view of the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, as well as the plenum chamber136and the forward flow valve150at the forward end88a, shown in circle8B ofFIG. 8A, where the inflatable cascade assembly80is coupled to a pressurized fluid supply system122via the forward flow valve150. As shown inFIG. 8B, the plenum chamber136comprises an orifice plate portion138coupled or attached at the forward end88aof the inflatable cascade assembly80. The plenum chamber136(seeFIG. 8B) is coupled or attached to the forward flow valve150(seeFIG. 8B) via inlet ducts126a(seeFIG. 8B).

As further shown inFIG. 8B, the forward flow valve150is preferably in the form of an electronic flow control valve150a, or another suitable type of flow control valve, and comprises a forward end152aand an aft end152b. As shown inFIG. 8B, the aft end152bof the forward flow valve150is coupled to the inlet ducts126a, and the forward end152aof the forward flow valve150is coupled to supply ducts124, which are, in turn, coupled or attached to the pressurized fluid supply system122having the pressurized fluid122.

As further shown inFIG. 8B, the inflatable cascade assembly80comprising the inflatable cascade member82, comprises the body90, the plurality of circumferential vanes92, and the plurality of inflatable support members102, such as the plurality of inflatable strongbacks102a. As further shown inFIG. 8B, each of the plurality of circumferential vanes92comprises the first non-inflatable rigid side94and the second inflatable flexible side96.

Now referring toFIG. 8C,FIG. 8Cis an illustration of a close-up side view of the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, as well as the translating aft cascade support ring140and the aft flow valve160at the aft end88b, shown in circle8C ofFIG. 8A, where the inflatable cascade assembly80is coupled to a plurality of pressure relief vents128via the aft flow valve160.

As shown inFIG. 8C, the translating aft cascade support ring140has a C-shaped configuration140b, and has a forward end142a, an aft end142b, and a body144formed between the forward end142aand the aft end142b. The translating aft cascade support ring140(seeFIG. 8C) is coupled or attached to the aft flow valve160(seeFIG. 8C) via outlet ducts126b(seeFIG. 8C).

As further shown inFIG. 8C, the aft flow valve160is preferably in the form of an electronic flow control valve160a, or another suitable type of flow control valve, and comprises a forward end162aand an aft end162b. As shown inFIG. 8C, the forward end162bof the aft flow valve160is coupled to the outlet ducts126b, and the aft end162bof the aft flow valve160is coupled to vent ducts127, which are, in turn, coupled or attached to the pressure relief vents128.

As further shown inFIG. 8C, the inflatable cascade assembly80comprising the inflatable cascade member82, comprises the body90, the plurality of circumferential vanes92, and the plurality of inflatable support members102, such as the plurality of inflatable strongbacks102a. As further shown inFIG. 8C, each of the plurality of circumferential vanes92comprises the first non-inflatable rigid side94and the second inflatable flexible side96.

Now referring toFIG. 9A,FIG. 9Ais an illustration of a partial sectional side view of a disclosed example of an inflatable cascade system10for an engine16, in a stowed position at forward thrust stage180. As shown inFIG. 9A, the nacelle14is in the form of a shortened nacelle14acomprising a reduced length translating portion170, such as a reduced length translating sleeve170a, that may be actuated or moved via thrust reverser actuators177, such as hydraulic actuators177a, and comprising a fixed portion174, such as an inlet cowl174a. The inflatable cascade system10(seeFIG. 9A) with the inflatable cascade assembly80(seeFIG. 9A) comprising the inflatable cascade member82(seeFIG. 9A), significantly reduces the length of the nacelle14(seeFIG. 9A), for example, the reduced length translating portion170(seeFIG. 9A), such as the reduced length translating sleeve170a(seeFIG. 9A), as compared to the longer known nacelle15(seeFIG. 9A) and the longer known translating portion50(seeFIG. 9A), such as the longer known translating sleeve50a(seeFIG. 9A), of the known nacelle15.

FIG. 9Afurther shows a cascade thrust reverser system24, such as an inflatable cascade thrust reverser system24a, having a cascade thrust reverser176, such as an inflatable cascade thrust reverser176a, in a stowed forward thrust mode181.FIG. 9Afurther shows a fan duct inner wall172aand a shortened fan duct outer wall172b, as compared to a longer known fan duct outer wall37b. InFIG. 9A, air flow33flows into the engine16, and becomes fan air flow33b, which flows past the thrust reverser bullnose fairing40, past the blocker doors48which are stored in a blocker door storage area146, and past the fan duct inner wall172aand the shortened fan duct outer wall172b. The blocker doors48are moved or deployed with a drag-link mechanism or another suitable deployment mechanism or apparatus.

FIG. 9Ashows the inflatable cascade system10with the inflatable cascade assembly80comprising the inflatable cascade member82in the stowed deflated state84.FIG. 9Afurther shows the forward end88a, the aft end88b, and the body90disposed between the forward end88aand the aft end88b, of the inflatable cascade member82, and shows the plurality of circumferential vanes92, the plurality of inflatable support members102, and the plenum chamber136at the forward end88aof the inflatable cascade assembly80.

As shown inFIG. 9A, the inflatable cascade system10further comprises the forward flow valve150, such as in the form of an electronic flow control valve150a, coupled to the forward end88aof the inflatable cascade assembly80, via the inlet ducts126a. As shown inFIG. 9A, in the stowed position at forward thrust stage180, the forward flow valve150is in a closed position156. The forward flow valve150(seeFIG. 9A) is preferably located at a forward location154(seeFIG. 9A) that is in a forward direction60(seeFIG. 9A) to the inflatable cascade assembly80(seeFIG. 9A).

As shown inFIG. 9A, the inflatable cascade system10further comprises the pressurized fluid supply system122coupled to the forward flow valve150via the supply ducts124. The pressurized fluid supply system122(seeFIG. 9A) contains the pressurized fluid120(seeFIG. 9A), which is configured to flow to the inflatable cascade assembly80, via the forward flow valve150, and inflate the inflatable cascade assembly80comprising the inflatable cascade member82.

As shown inFIG. 9A, the inflatable cascade system10further comprises the translating aft cascade support ring140coupled at the aft end88bof the inflatable cascade assembly80. The translating aft cascade support ring140(seeFIG. 9A) is coupled to a translating apparatus148(seeFIG. 9A), such as in the form of a slider apparatus148a(seeFIG. 9A).

As shown inFIG. 9A, the inflatable cascade system10further comprises the aft flow valve160, such as in the form of an electronic flow control valve160a, coupled to the aft end88bof the inflatable cascade assembly80, via the outlet ducts126b. As shown inFIG. 9A, in the stowed position at forward thrust stage180, the aft flow valve160is in a closed position166. The aft flow valve160(seeFIG. 9A) is preferably located at an aft location164(seeFIG. 9A) that is in an aft direction62(seeFIG. 9A) to the inflatable cascade assembly80(seeFIG. 9A). The aft flow valve160(seeFIG. 9A) is coupled to one or more vent ducts127(seeFIG. 9A) that are coupled to one or more pressure relief vents128(seeFIG. 9A).

Thus, in the operation of the inflatable cascade system10(seeFIGS. 4, 9A-9D), during the stowed position at forward thrust stage180(seeFIG. 9A) and the stowed forward thrust mode181(seeFIG. 9A), i.e., stowed position: 0% deployed, the inflatable cascade assembly80(seeFIGS. 4, 9A) remains in the stowed deflated state84(seeFIG. 6A), or flat position, and enables a compact design for the reduced length translating sleeve170a(seeFIGS. 4, 9A).

Now referring toFIG. 9B,FIG. 9Bis an illustration of a partial sectional side view of the inflatable cascade system10ofFIG. 9Afor the engine16, in a stowed position after landing and prior to thrust reverser deployment stage182. In this stowed position after landing and prior to thrust reverser deployment stage182(seeFIG. 9B), the forward flow valve150(seeFIG. 9B), such as in the form of the electronic flow control valve150a(seeFIG. 9B), is opened from the closed position156(seeFIG. 9A) to an open position158(seeFIG. 9B), so that the pressurized fluid120(seeFIG. 9B), from the pressurized fluid supply system122(seeFIG. 9B), can flow through the supply ducts124(seeFIG. 9B), through the forward flow valve150(seeFIG. 9B) in the open position158(seeFIG. 9B), and into the inflatable cascade assembly80(seeFIG. 9B) via the inlet ducts126aThe pressurized fluid120(seeFIG. 9B) may comprise pressurized air120a(seeFIG. 4), engine compressor bleed air120b(seeFIG. 4), compressed air120c(see FIG.4), hydraulic fluid120d(seeFIG. 4), ram air120e(seeFIG. 4), or another suitable pressurized fluid120.

During the stowed position after landing and prior to thrust reverser deployment stage182(seeFIG. 9B), the pressurized fluid120(seeFIGS. 4, 9B), for example, the engine compressor bleed air120b(seeFIG. 4) from the engine's16(seeFIG. 4) high pressure compressor, i.e., fourth stage or tenth stage, is preferably fed to the inflatable cascade assembly80(seeFIGS. 4, 9B) in the stowed deflated state84(seeFIG. 9B), via the plenum chamber136(seeFIG. 9B), and is regulated using the forward flow valve150(seeFIGS. 4, 9B). In another example, the pressurized fluid120(seeFIG. 4) may comprise compressed air120c(seeFIG. 4) supplied from a compressed air supply system122c(seeFIG. 4), such as one or more compressed air bottles122d(seeFIG. 4).

As shown inFIG. 9B, the nacelle14, such as the shortened nacelle14a, comprises the reduced length translating portion170, such as the reduced length translating sleeve170a, which is actuated or moved via the thrust reverser actuators177, such as hydraulic actuators177a, in the aft direction62and in the forward direction60. The nacelle14(seeFIG. 9B) further comprises the fixed portion174, such as the inlet cowl174a.

As discussed above, the inflatable cascade system10(seeFIG. 9B) with the inflatable cascade assembly80(seeFIG. 9B) comprising the inflatable cascade member82(seeFIG. 9B), significantly reduces the length of the nacelle14(seeFIG. 9B), for example, the reduced length translating portion170(seeFIG. 9B), such as the reduced length translating sleeve170a(seeFIG. 9B), as compared to the longer known nacelle15(seeFIG. 9B) and the longer known translating portion50(seeFIG. 9B), such as the longer known translating sleeve50a(seeFIG. 9B), of the known nacelle15.

The cascade thrust reverser system24(seeFIG. 9B), such as the inflatable cascade thrust reverser system24a(seeFIG. 9B), having the cascade thrust reverser176(seeFIG. 9B), such as the inflatable cascade thrust reverser176a(seeFIG. 9B), is still in the stowed forward thrust mode181(seeFIG. 9B).FIG. 9Bfurther shows the fan duct inner wall172aand the shortened fan duct outer wall172b, as compared to the longer known fan duct outer wall37b. InFIG. 9B, the air flow33still flows into the engine16, and becomes fan air flow33b, which flows past the thrust reverser bullnose fairing40, past the blocker doors48stored in the blocker door storage area146, and past the fan duct inner wall172aand the shortened fan duct outer wall172b. The blocker doors48(seeFIG. 9B) are moved or deployed with a drag-link mechanism or another suitable deployment mechanism or apparatus.

FIG. 9Bshows the inflatable cascade system10with the inflatable cascade assembly80comprising the inflatable cascade member82still in the stowed deflated state84.FIG. 9Bfurther shows the plurality of circumferential vanes92, the plurality of inflatable support members102, and the plenum chamber136. As shown inFIG. 9B, the inflatable cascade system10further comprises the translating aft cascade support ring140coupled to the translating apparatus148(seeFIG. 9B), such as in the form of the slider apparatus148a(seeFIG. 9B).

As the inflatable cascade assembly80(seeFIGS. 4, 9C) translates and deploys to perform a thrust reverser operation, the translating aft cascade support ring140(seeFIGS. 4, 9C) slides over the translating apparatus148(seeFIG. 4, 9C), such as the slider apparatus148a(seeFIGS. 4, 9C), using the thrust reverser actuators177(seeFIGS. 4, 9C), such as the hydraulic actuators177a(seeFIGS. 4, 9C), or another suitable actuator, and the inflatable cascade assembly80comprising the inflatable cascade member82(seeFIGS. 4, 9C) gets pressurized by the pressurized fluid120(seeFIGS. 4, 9C) supplied from the pressurized fluid supply system122(seeFIGS. 4, 9C) and assumes a similar shape to the solid cascades. During this transition, the aft flow valve160(seeFIGS. 4, 9C) remains closed in the closed position166(seeFIG. 9C).

As shown inFIG. 9B, the aft flow valve160, such as in the form of the electronic flow control valve160a, is coupled to the inflatable cascade assembly80, via the outlet ducts126b. The aft flow valve160(seeFIG. 9B) is coupled to the one or more vent ducts127(seeFIG. 9B) that are coupled to the one or more pressure relief vents128(seeFIG. 9B). As shown inFIG. 9B, in the stowed position after landing and prior to thrust reverser deployment stage182, the aft flow valve160is still in the closed position166.

Now referring toFIG. 9C,FIG. 9Cis an illustration of a partial sectional side view of the inflatable cascade system10ofFIG. 9Afor the engine16, in a fully deployed position at reverse thrust stage184. In this fully deployed position at reverse thrust stage184(seeFIG. 9C), the forward flow valve150(seeFIG. 9C), such as in the form of the electronic flow control valve150a(seeFIG. 9C), is closed slightly, so that it is in a semi-open position157(seeFIG. 9C), and the aft flow valve160(seeFIG. 9C), such as in the form of the electronic flow control valve160a(seeFIG. 9C), is still in the closed position166(seeFIG. 9C). With the forward flow valve150(seeFIG. 9C) in the semi-open position157(seeFIG. 9C), the pressurized fluid120(seeFIG. 9C) from the pressurized fluid supply system122(seeFIG. 9C) can still flow through the supply ducts124(seeFIG. 9C), through the forward flow valve150, and into the inflatable cascade assembly80(seeFIG. 9C).

As shown inFIG. 9C, the nacelle14, such as the shortened nacelle14a, comprises the reduced length translating portion170, such as the reduced length translating sleeve170a, which is actuated or deployed via the thrust reverser actuators177, such as hydraulic actuators177a, in a deployment direction185, such as the aft direction62. The nacelle14(seeFIG. 9C) further comprises the fixed portion174(seeFIG. 9C), such as the inlet cowl174a(seeFIG. 9C), which is fixed and does not translate in the aft direction62(seeFIG. 9C). As shown inFIG. 9C, the thrust reverser actuator177is attached at a one end which is fixed to the fixed portion174and is attached at another translating end to the reduced length translating portion170.

As discussed above, the inflatable cascade system10(seeFIG. 9C) with the inflatable cascade assembly80(seeFIG. 9C) comprising the inflatable cascade member82(seeFIG. 9C), significantly reduces the length of the nacelle14(seeFIG. 9C). For example, the reduced length translating portion170(seeFIG. 9C), such as the reduced length translating sleeve170a(seeFIG. 9C), is shorter in length, as compared to the longer known nacelle15(seeFIG. 9C) and the longer known translating portion50(seeFIG. 9C), such as the longer known translating sleeve50a(seeFIG. 9C), of the known nacelle15.

The cascade thrust reverser system24(seeFIG. 9C), such as the inflatable cascade thrust reverser system24a(seeFIG. 9C), having the cascade thrust reverser176(seeFIG. 9C), such as the inflatable cascade thrust reverser176a(seeFIG. 9C), is shown in a deployed reverse thrust mode186(seeFIG. 9C).FIG. 9Cfurther shows the fan duct inner wall172aand the shortened fan duct outer wall172b, as compared to the longer known fan duct outer wall37b. InFIG. 9C, the air flow33, such as in the form of fan air flow33b, cannot flow past the blocker doors48which are now deployed, and is diverted or deflected past the thrust reverser bullnose fairing40, and through the inflatable cascade assembly80comprising the inflatable cascade member82, and in particular, through the plurality of circumferential vanes92and through the plurality of inflatable support members102, such as the plurality of strongbacks102a. As shown inFIG. 9C, the inflatable cascade assembly80is in a deployed inflated state86. The fan air flow33b(seeFIG. 9C) flows through the inflatable cascade assembly80(seeFIG. 9C) which turns the fan air flow33bas it exits out of the engine16(seeFIG. 9C) to become reverse efflux air flow33c(seeFIG. 9C) which flows out in a generally forward direction60(seeFIG. 9C) and generates the thrust reverser effect.

FIG. 9Cshows the inflatable cascade system10with the inflatable cascade assembly80comprising the inflatable cascade member82in the deployed inflated state86, where the inflatable cascade member82has trapped fluid189when in the deployed inflated state86.FIG. 9Cfurther shows the plenum chamber136and the translating aft cascade support ring140coupled to the translating apparatus148, such as in the form of the slider apparatus148a(seeFIG. 9B).

As shown inFIG. 9C, the aft flow valve160, such as in the form of the electronic flow control valve160a, is coupled to the inflatable cascade assembly80, via the outlet ducts126b. The aft flow valve160(seeFIG. 9C) is coupled to the one or more vent ducts127(seeFIG. 9C) that are coupled to the one or more pressure relief vents128(seeFIG. 9C).

Thus, at the fully deployed position at reverse thrust stage184(seeFIG. 9C), the reduced length translating sleeve170a(seeFIG. 9C) is fully deployed, along with the fully deployed blocker doors48(seeFIG. 9C), and the inflatable cascade assembly80(seeFIG. 9C) comprising the inflatable cascade member82(seeFIG. 9C), turns the fan air flow33b(seeFIG. 9C) as it exits the engine16(seeFIG. 9C) to become reverse efflux air flow33c(seeFIG. 9C) to generate the reverse thrust and slow down the air vehicle12(seeFIG. 1) such as the aircraft12a(seeFIG. 1) by generating the aerodynamic breaking.

Now referring toFIG. 9D,FIG. 9Dis an illustration of a partial sectional side view of the inflatable cascade system10ofFIG. 9Afor the engine16, in a deployed position prior to thrust reverser stowing stage188. In this deployed position prior to thrust reverser stowing stage188(seeFIG. 9D), the forward flow valve150(seeFIG. 9D), such as in the form of the electronic flow control valve150a(seeFIG. 9D), is now closed and in the closed position156, so that no additional pressurized fluid120(seeFIG. 9D) from the pressurized fluid supply system122(seeFIG. 9D) can flow through the supply ducts124(seeFIG. 9D), into and through the forward flow valve150, through the plenum chamber136, and into the inflatable cascade assembly80.

In addition, in this deployed position prior to thrust reverser stowing stage188(seeFIG. 9D), the aft flow valve160(seeFIG. 9D), such as in the form of the electronic flow control valve160a(seeFIG. 9D), is now opened and in an open position168(seeFIG. 9D). As shown inFIG. 9D, with the aft flow valve160in the open position168, the trapped fluid189, or deflated pressurized fluid or deflated air, in the inflatable cascade assembly80comprising the inflatable cascade member82, flows out of the inflatable cascade assembly80, through the outlet ducts126b, through the aft flow valve160, which is now open, and is vented through the vent ducts127disposed in a cavity187of the reduced length translating sleeve170a, and is vented out of the engine16. The trapped fluid189(seeFIG. 9D), or deflated pressurized fluid or deflated air, may be vented out of cavity187and out of the pressure relief vents128(seeFIG. 9D) in the nacelle14(seeFIG. 9D) to relieve the pressure inside the cavity187(seeFIG. 9D) during taxiing of the aircraft12a(seeFIG. 1) on the runway.

In addition, in this deployed position prior to thrust reverser stowing stage188(seeFIG. 9D), the translating aft cascade support ring140(seeFIG. 9D) begins translating or sliding via the translating apparatus148(seeFIG. 9D), such as the slider apparatus148a(seeFIG. 9D), back toward the stowed position at forward thrust stage180(seeFIG. 9A). In this deployed position prior to thrust reverser stowing stage188(seeFIG. 9D), the blocker doors48(seeFIG. 9D) are still in the deployed position before going back to being stowed in the blocker door storage area146(seeFIG. 9D).

FIG. 9Dfurther shows the nacelle14, such as the shortened nacelle14a, comprising the reduced length translating portion170, such as the reduced length translating sleeve170a, which is actuated or deployed via the thrust reverser actuators177, such as hydraulic actuators177a.FIG. 9Dfurther shows the fixed portion174(seeFIG. 9C), such as the inlet cowl174a(seeFIG. 9C), of the nacelle14.

As discussed above, the inflatable cascade system10(seeFIG. 9D) with the inflatable cascade assembly80(seeFIG. 9D) comprising the inflatable cascade member82(seeFIG. 9D), significantly reduces the length of the nacelle14(seeFIG. 9D), and the reduced length translating portion170(seeFIG. 9D), such as the reduced length translating sleeve170a(seeFIG. 9C), is shorter in length, as compared to the longer known nacelle15(seeFIG. 9D) and the longer known translating portion50(seeFIG. 9D), such as the longer known translating sleeve50a(seeFIG. 9D), of the known nacelle15.

The cascade thrust reverser system24(seeFIG. 9D), such as the inflatable cascade thrust reverser system24a(seeFIG. 9D), having the cascade thrust reverser176(seeFIG. 9C), such as the inflatable cascade thrust reverser176a(seeFIG. 9D), is still shown in the deployed reverse thrust mode186(seeFIG. 9D).FIG. 9Dfurther shows the fan duct inner wall172aand the shortened fan duct outer wall172b, as compared to the longer known fan duct outer wall37b. InFIG. 9D, the air flow33, such as in the form of fan air flow33b, cannot flow past the blocker doors48which are still deployed, and is diverted or deflected past the thrust reverser bullnose fairing40, and through the plurality of circumferential vanes92and the plurality of inflatable support members102, such as the plurality of strongbacks102a, of the inflatable cascade assembly80. As shown inFIG. 9D, the inflatable cascade assembly80is still in the deployed inflated state86. The fan air flow33b(seeFIG. 9D) flows through the inflatable cascade assembly80(seeFIG. 9D), which turns the fan air flow33bas it exits out of the engine16(seeFIG. 9D) to become the reverse efflux air flow33c(seeFIG. 9D) which flows out in a generally forward direction60(seeFIG. 9D) and generates the thrust reverser effect.

Succeeding the thrust reverser operation, and at the deployed position prior to thrust reverser stowing stage188(seeFIG. 9D), the forward flow valve150(seeFIG. 9D) closes and the aft flow valve160(seeFIG. 9D) opens to release the trapped fluid189(seeFIG. 9D), such as trapped pressurized air, from the inflated inflatable cascade assembly80(seeFIG. 9D) comprising the inflated inflatable cascade member82(seeFIG. 9D).

Once all of the trapped fluid189(seeFIG. 9D) flows out of the inflatable cascade assembly80(seeFIG. 9D), the aft flow valve160may be closed back to the closed position166(seeFIG. 9A), and the inflatable cascade assembly80may be moved from the aft direction62(seeFIG. 9D) to the forward direction60(seeFIG. 9D), via the translating aft cascade support ring140(seeFIG. 9D) and the translating apparatus148(seeFIG. 9D), and back to the stowed position at forward thrust stage180(seeFIG. 9A). In addition, the reduced length translating portion170(seeFIG. 9D), such as the reduced length translating sleeve170a(seeFIG. 9D), may be moved from the aft direction62(seeFIG. 9D) to the forward direction60(seeFIG. 9D), via the thrust reverser actuators177(seeFIG. 9D), such as the hydraulic actuators177a, and back to the stowed position at forward thrust stage180(seeFIG. 9A). In addition, the cascade thrust reverser176, such as the inflatable cascade thrust reverser176a, may be moved from the aft direction62(seeFIG. 9D) to the forward direction60(seeFIG. 9D), and back to the stowed forward thrust mode181(seeFIG. 9A). In addition, the blocker doors48(seeFIG. 9D) may be moved or deployed via a drag-link mechanism or another suitable deployment mechanism or apparatus back into the blocker door storage area146(seeFIG. 9D), and back to the stowed position at forward thrust stage180(seeFIG. 9A).

During this stowing transition from 100% deployed to 0% deployed, the translating aft cascade support ring140(seeFIG. 9D) starts sliding again to its stowed position. Meanwhile, the trapped fluid189(seeFIG. 9D) continues to escape from the inflated inflatable cascade assembly80(seeFIG. 9D) comprising the inflated inflatable cascade member82(seeFIG. 9D), via the open aft flow valve160(seeFIG. 9D). This escaped trapped fluid189(seeFIG. 9D) flows into the cavity187(seeFIG. 9D) of the reduced length translating sleeve170a(seeFIG. 9D) and then exits the cavity187(seeFIG. 9D) via the pressure relief vents128(seeFIG. 9D) located on the external translating sleeve (one pressure relief vent per translating sleeve).

At the end, the cascade thrust reverser176(seeFIG. 9A) is again back at the stowed position at forward thrust stage180(seeFIG. 9A) and regains its stowed forward thrust mode181(seeFIG. 9A), i.e., 0% stowed position, where the inflatable cascade assembly80(seeFIG. 9A) comprising the inflated inflatable cascade member82(seeFIG. 9A) is again back in the stowed deflated state84(seeFIG. 9A), and the cascades are fully flat. The blocker doors48(seeFIG. 9A) and the reduced length translating sleeve170a(seeFIG. 9A) are also transitioned to their respective fully stowed positions.

Now referring toFIG. 10,FIG. 10is an illustration of a partial sectional side view of the inflatable cascade system10ofFIG. 9C, in the deployed reverse thrust mode186, showing a disclosed example of one or more safety devices190that may be used with the inflatable cascade system10. The one or more safety devices190(seeFIGS. 4, 10) preferably comprise one or more pressure sensors190a(seeFIG. 4) configured to signal one or more of, an air leakage191a(seeFIG. 4) in the inflatable cascade system10, a cascade breach191b(seeFIG. 4) of one or more of the plurality of inflatable cascade members82(seeFIGS. 4, 10), or another safety issue. The safety devices190(seeFIG. 4) may further comprise transducers, electrical signals, alarms, or other safety devices or safety notification devices.

As shown inFIG. 10, in the deployed reverse thrust mode186, a delta pressure196(ΔP) may be constantly measured across a forward flow pressure192(PFwd) from the forward flow valve150, such as the electronic flow control valve150a, and an aft flow pressure194(PAft) from the aft flow valve160, such as the electronic flow control valve160a. As further shown inFIG. 10, if any leakage, such as air leakage191a(seeFIG. 4), is detected, for example, there is a drop or decrease in the delta pressure196(ΔP) and/or the delta pressure196(ΔP) is less than a calibrated value of pressure, then an electronic signal197preferably triggers one or more commands198to stow the cascade thrust reverser176, such as the inflatable cascade thrust reverser176a, and to stow other structures or components of the engine16. The safety devices190are commands198are discussed in further detail below with respect toFIG. 11.

In addition, during the stowed forward thrust mode181(seeFIG. 9A), to eliminate or minimize any unwanted inflation191c(seeFIG. 4), or pressurization, due to any possible issues or problems with the forward flow valve150(seeFIGS. 9A, 10), the aft flow valve160(seeFIGS. 9A, 9D, 10) may be kept open in the open position168(seeFIG. 9D).

FIG. 10further shows the fully deployed position at reverse thrust stage184ofFIG. 9Cwith the forward flow valve150in the semi-open position157, so that the pressurized fluid120from the pressurized fluid supply system122can still flow through the supply ducts124, through the forward flow valve150, and into the inflatable cascade assembly80, and with the aft flow valve160in the closed position166.FIG. 10further shows the nacelle14, such as the shortened nacelle14a, comprising the reduced length translating portion170, such as the reduced length translating sleeve170a, which is actuated or deployed via the thrust reverser actuators177, such as hydraulic actuators177a.FIG. 10further shows the fixed portion174, such as the inlet cowl174a, of the nacelle14, the cascade thrust reverser176, such as the inflatable cascade thrust reverser176a, the fan duct inner wall172aand the shortened fan duct outer wall172b, as compared to the longer known fan duct outer wall37b, and further shows the air flow33, such as in the form of fan air flow33bbeing blocked by the blocker doors48and diverted or deflected past the thrust reverser bullnose fairing40, and through the plurality of circumferential vanes92and the plurality of inflatable support members102, such as the plurality of strongbacks102a, of the inflatable cascade assembly80. As shown inFIG. 10, the inflatable cascade assembly80is in the deployed inflated state86, and the fan air flow33bflows through the inflatable cascade assembly80, which turns the fan air flow33bas it exits out of the engine16to become the reverse efflux air flow33cwhich flows out in the generally forward direction60and generates the thrust reverser effect. As discussed above the reduced length translating portion170(seeFIG. 10), such as the reduced length translating sleeve170a(seeFIG. 10), is shorter in length, as compared to the longer known nacelle15(seeFIG. 10) and the longer known translating portion50(seeFIG. 10), such as the longer known translating sleeve50a(seeFIG. 10), of the known nacelle15.

Now referring toFIG. 11,FIG. 11is an illustration of a schematic flow diagram for a disclosed example of an inflatable cascade system command and hardware scheme200for a cascade thrust reverser system24, such as an inflatable cascade thrust reverser system24a.FIG. 11shows a command indicator202, a pressurized fluid flow indicator204, a mechanical action indicator206, a safety feature indicator208, and a hardware indicator210for the inflatable cascade system command and hardware scheme200.

As shown inFIG. 11, the inflatable cascade system command and hardware scheme200starts with a pilot or user using a command hardware212to issue a deploy or stow control command214for commanding the cascade thrust reverser system24, such as the inflatable cascade thrust reverser system24. When the deploy or stow control command214(seeFIG. 11) is made, hardware216(seeFIG. 11) is activated, such as for control of the engine16(seeFIGS. 1, 4), control of high-lift surfaces of the aircraft12a(seeFIGS. 1, 4), or other aircraft controls pertinent to the thrust reverser actuators177(seeFIGS. 4, 9A), the cascade thrust reverser176(seeFIGS. 4, 9A), such as the inflatable cascade thrust reverser176a(seeFIGS. 4, 9A), the inflatable cascade assembly80(seeFIGS. 4, 9A-9D), and the inflatable cascade members82(seeFIGS. 4, 9A-9D).

As further shown inFIG. 11, a power and control command218is issued to a thrust reverser actuator hardware220to provide power and control to deploy (or stow) the thrust reverser actuators177(seeFIGS. 3, 9A). As further shown inFIG. 11, a translating sleeve and blocker door command222is made to a translating sleeve and blocker door hardware224to deploy or stow the reduced length translating sleeve170a(seeFIGS. 3, 9A-9D) and the blocker doors48(seeFIGS. 9A-9D).

As further shown inFIG. 11, a translating aft cascade support ring command226is made to a translating aft cascade support ring hardware228to deploy or stow the translating aft cascade support ring140(seeFIGS. 3, 9A), by moving or sliding the translating aft cascade support ring140(seeFIGS. 3, 9A) with the translating apparatus148(seeFIGS. 3, 9A), such as the slider apparatus148a(seeFIGS. 3, 9A-9D). Preferably, the translating sleeve and blocker door hardware224(seeFIG. 11) is activated first, and then a successive command230(seeFIG. 11), such as the translating aft cascade support ring command226(seeFIG. 11) is made and the translating aft cascade support ring hardware228(seeFIG. 11) is activated.

Once the translating sleeve and blocker door hardware224(seeFIG. 11) and the translating aft cascade support ring hardware228(seeFIG. 11) are activated, the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) is inflated by commanding with a pressurized fluid supply system command232(seeFIG. 11) a pressurized fluid supply system hardware234(seeFIG. 11) to release a pressurized fluid flow236(seeFIG. 11), and a forward flow valve command238(seeFIG. 11) is made to a forward flow valve hardware240to open the forward flow valve150(seeFIGS. 4, 9B) to an open position158(seeFIG. 9B).

As further shown inFIG. 11, once the forward flow valve150(seeFIGS. 4, 9B) is in the open position158(seeFIG. 9B), pressurized fluid120(seeFIGS. 4, 9B) flows as forward flow valve pressurized fluid flow236from the pressurized fluid supply system hardware234, such as the pressurized fluid supply system122(seeFIGS. 4, 9B), to the forward flow valve hardware240, such as the forward flow valve150(seeFIGS. 4, 9B), and then flows as inflatable cascade assembly pressurized fluid flow242from the forward flow valve hardware240, such as the forward flow valve150(seeFIGS. 4, 9B), to an inflatable cascade assembly hardware244, such as in the form of the inflatable cascade assembly80(seeFIGS. 4, 9B) comprising the inflatable cascade member82(seeFIGS. 4, 9B).

Preferably, the translating sleeve and blocker door hardware224(seeFIG. 11) and the translating aft cascade support ring hardware228(seeFIG. 11) are activated, and then one or more commands246, that may be successive or simultaneous, such as the pressurized fluid supply system command232and the forward flow valve command238, may be made, and the inflatable cascade assembly hardware244(seeFIG. 11) is activated. After the inflatable cascade assembly80(seeFIGS. 4, 9C) is fully deployed and after the cascade thrust reverser system24, such as the inflatable cascade thrust reverser system24a, has undergone the reverse thrust operation, the forward flow valve command238(seeFIG. 11) is made to the forward flow valve hardware240(seeFIG. 11) to close the forward flow valve150(seeFIGS. 4, 9A, 9D) to the closed position156(seeFIGS. 9A, 9D), and an aft flow valve command250(seeFIG. 11) is made to an aft flow valve hardware252(seeFIG. 11) to open the aft flow valve160(seeFIGS. 4, 9D) to an open position168(seeFIG. 9D), to release a trapped pressurized fluid flow254(seeFIG. 11) from the inflatable cascade assembly80(seeFIG. 9D), and vent the trapped pressurized fluid flow254(seeFIG. 11) out of the cascade thrust reverser system24, such as an inflatable cascade thrust reverser system24a.

As further shown inFIG. 11, the inflatable cascade system command and hardware scheme200shows the safety feature, as discussed above with regard toFIG. 10, of a forward pressure sensor hardware258which measures a forward pressure sensor pressurized fluid flow256from the forward flow valve150(seeFIGS. 4, 9C), and an aft pressure sensor hardware264which measures an aft pressure sensor pressurized fluid flow262from the aft flow valve160(seeFIGS. 4, 9C). As further shown inFIG. 11, a delta pressure measurement hardware268is constantly measured across the forward flow valve150(seeFIGS. 4, 9C) and the aft flow valve160(seeFIGS. 4, 9C), via a forward pressure sensor signal260and an aft pressure sensor signal266. If any pressurized fluid leakage, such as air leakage191a(seeFIG. 4), is detected, for example, there is a drop in pressure, an electronic signal197(seeFIG. 10) is generated and triggers one or more commands198(seeFIG. 10), such as a safety feature thrust reverser stow command270, to stow the thrust reverser actuator hardware220, such as the thrust reverser actuators177(seeFIGS. 3, 9A), and triggers a first safety feature engine and high-lift surfaces stow command271(seeFIG. 11) to stow the hardware216(seeFIG. 11).

As further shown inFIG. 11, if any pressurized fluid leakage, such as air leakage191a(seeFIG. 4), is detected, for example, there is a drop in pressure, the electronic signal197(seeFIG. 10) is generated and may trigger a safety feature pressurized fluid supply system stop command272to the pressurized fluid supply system hardware234to stop the forward flow valve pressurized fluid flow236from the pressurized fluid supply system hardware234, such as the pressurized fluid supply system122(seeFIGS. 4, 9C), and triggers a second safety feature engine and high-lift surfaces stow command273to stow the hardware216.

Now referring toFIG. 12, in another disclosed example, there is provided a method280of using an inflatable cascade system10(seeFIGS. 4, 9A-9D) for a cascade thrust reverser system24(seeFIGS. 4, 9A-9D) in an engine16(seeFIGS. 1, 4) of an air vehicle12(seeFIGS. 1, 4), to provide a reduced aerodynamic drag274(seeFIG. 4) of the engine16(seeFIG. 4) and to provide an increased fan nozzle efficiency277(seeFIG. 4) of the engine16(seeFIG. 4), as well as an increased fan duct efficiency276(seeFIG. 4).FIG. 12is an illustration of a flow diagram showing a disclosed example of the method280.

As shown inFIG. 12, the method280comprises step282of installing the inflatable cascade system10(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), in the engine16(seeFIGS. 4, 9A-9D) of the air vehicle12(seeFIGS. 1, 4). As discussed in detail above, the inflatable cascade system10(seeFIGS. 4, 9A-9D) comprises the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) coupled to the fixed portion174(seeFIGS. 4, 9A-9D) of the nacelle14(seeFIGS. 4, 9A-9D), such as the shortened nacelle14a(seeFIGS. 4, 9A-9D) of the engine16. The inflatable cascade assembly80comprises a plurality of inflatable cascade members82(seeFIGS. 4, 9A-9D) movable between a stowed deflated state84(seeFIGS. 4, 6A), when the cascade thrust reverser system24(seeFIGS. 4, 9A-9D) is in a stowed forward thrust mode181(seeFIGS. 9A-9B), and a deployed inflated state86(seeFIGS. 4, 5A), when the cascade thrust reverser system24is in a deployed reverse thrust mode186(seeFIGS. 9C-9D).

As shown inFIG. 5A, each inflatable cascade member82comprises the forward end88a, the aft end88b, and the body90formed between the forward end88aand the aft end88b. The inflatable cascade system10(seeFIGS. 4, 9A-9D) further comprises the forward flow valve150, such as in the form of an electronic flow control valve150a(seeFIGS. 4, 9A-9D), coupled to the forward end88a(seeFIG. 9A).

The inflatable cascade system10(seeFIGS. 4, 9A-9D) further comprises the pressurized fluid supply system122(seeFIGS. 4, 9A-9D) coupled to the forward flow valve150(seeFIGS. 4, 9A-9D). The pressurized fluid supply system122(seeFIGS. 4, 9A-9D) provides pressurized fluid120(seeFIGS. 4, 9A-9D) to the plurality of inflatable cascade members82(seeFIGS. 4, 9A-9D), via the forward flow valve150(seeFIGS. 4, 9A-9D), to inflate the plurality of inflatable cascade members82.

The inflatable cascade system10(seeFIGS. 4, 9A-9D) further comprises a translating aft cascade support ring140(seeFIGS. 4, 9A-9D) coupled at the aft end88b(seeFIG. 5A, 9A). The inflatable cascade system10(seeFIGS. 4, 9A-9D) further comprises an aft flow valve160(seeFIG. 9A) coupled to the aft end88b(seeFIG. 9A).

The step282(seeFIG. 12) of installing the inflatable cascade system10(seeFIGS. 4, 9A-9D) in the engine16of the air vehicle12further comprises installing the inflatable cascade assembly80further comprising a plenum chamber136coupled at the forward end88aof each inflatable cascade member82, to distribute the pressurized fluid120uniformly within each inflatable cascade member82. The pressurized fluid120(seeFIGS. 4, 9A-9D) may comprise one of, pressurized air120a(seeFIG. 4), engine compressor bleed air120b(seeFIG. 4), compressed air120c(seeFIG. 4), hydraulic fluid120d(seeFIG. 4), ram air120e(seeFIG. 4), or another suitable pressurized fluid120(seeFIG. 4).

The step282(seeFIG. 12) of installing the inflatable cascade system10(seeFIGS. 4, 9A-9D) in the engine16(seeFIGS. 1, 4) of the air vehicle12(seeFIGS. 1, 4) further comprises installing one or more safety devices190(seeFIGS. 4, 10). The safety devices190(seeFIGS. 4, 10) preferably comprise one or more pressure sensors190a(seeFIG. 4) configured to signal one or more of, an air leakage191a(seeFIG. 4) in the inflatable cascade system10, a cascade breach191b(seeFIG. 4) of one or more of the plurality of inflatable cascade members82(seeFIG. 4), or another safety issue. The safety devices190(seeFIGS. 4, 10) may further comprise transducers, electrical signals, alarms, or other suitable safety devices or safety notification devices.

The step282(seeFIG. 12) of installing the inflatable cascade system10(seeFIGS. 4, 9A-9D) in the engine16(seeFIGS. 1, 4) of the air vehicle12(seeFIGS. 1, 4) further comprises installing the inflatable cascade assembly80(seeFIGS. 4, 9A), wherein the translating aft cascade support ring140(seeFIGS. 4, 9A) is coupled to a translating apparatus148(seeFIGS. 4, 9A) configured to move the translating aft cascade support ring140, which, in turn, is configured to move the plurality of inflatable cascade members82(seeFIGS. 4, 9A) between the stowed deflated state84(seeFIGS. 4, 6A, 9A) and the deployed inflated state86(seeFIGS. 4, 5A, 9C), to elongate with deployment and shorten with stowing the plurality of inflatable cascade members82(seeFIGS. 4, 5A, 6A, 9A, 9C).

The step282(seeFIG. 2) of installing the inflatable cascade system10(seeFIGS. 4, 9A-9D) in the engine16(seeFIGS. 1, 4) of the air vehicle12(seeFIGS. 1, 4) further comprises installing the inflatable cascade assembly80(seeFIG. 4), wherein each of the plurality of inflatable cascade members82(seeFIGS. 4, 9A) has a stowed length85(seeFIGS. 4, 6A), when in the stowed deflated state84(seeFIGS. 4, 6A), that is about 15% (fifteen percent) to about 25% (twenty-five percent) of a total deployed length87(seeFIGS. 4, 5A) of the inflatable cascade member82(seeFIGS. 4, 5A), when the inflatable cascade member82is in the deployed inflated state86(seeFIGS. 4, 5A).

As shown inFIG. 12, the method280further comprises step284of, upon landing or touchdown on the ground surface, such as a runway of an airport, by the air vehicle12(seeFIGS. 1, 4), concurrently deploying from the stowed forward thrust mode181(seeFIG. 9A), the translating aft cascade support ring140(seeFIG. 9A), and the reduced length translating sleeve170a(seeFIG. 9A) and one or more blocker doors48(seeFIG. 9A), of the cascade thrust reverser system24(seeFIG. 9A).

As shown inFIG. 12, the method280further comprises step286of opening the forward flow valve150(seeFIG. 9B) in the open position158(seeFIG. 9B), and fully inflating the plurality of inflatable cascade members82(seeFIG. 9C) with the pressurized fluid120(seeFIG. 9C) from the pressurized fluid supply system122(seeFIG. 9C), to form a trapped fluid189(seeFIG. 9C) in the plurality of inflatable cascade members82(seeFIG. 9C), and to move the plurality of inflatable cascade members82from the stowed deflated state84(seeFIG. 9B) to the deployed inflated state86(seeFIG. 9C).

The step286(seeFIG. 12) of opening the forward flow valve150(seeFIG. 9C) and fully inflating the plurality of inflatable cascade members82(seeFIG. 9C) with the pressurized fluid120(seeFIG. 9C) from the pressurized fluid supply system122(seeFIG. 9C), comprises fully inflating the plurality of inflatable cascade members82(seeFIG. 9C) with the pressurized fluid120(seeFIG. 9C) comprising one of, pressurized air120a(seeFIG. 4), engine compressor bleed air120b(seeFIG. 4), compressed air120c(seeFIG. 4), hydraulic fluid120d(seeFIG. 4), ram air120e(seeFIG. 4), or another suitable pressurized fluid120(seeFIG. 4).

As shown inFIG. 12, the method280further comprises step288of redirecting the fan air flow33b(seeFIG. 9C) with the fully inflated plurality of inflatable cascade members82(seeFIG. 9C) and with the one or more deployed blocker doors48(seeFIG. 9C), to generate the deployed reverse thrust mode186(seeFIG. 9C) of the cascade thrust reverser system24(seeFIG. 9C). The plurality of inflatable cascade members82(seeFIG. 9C) in the deployed inflated state86(seeFIG. 9C) redirect and divert the fan air flow33b(seeFIG. 9C) out of the engine16(seeFIG. 9C), as reverse efflux air flow33c(seeFIG. 3C) to generate reverse thrust.

As shown inFIG. 12, the method280further comprises step290of closing the forward flow valve150(seeFIG. 9D) so that it is in the closed position156(seeFIG. 9D), and opening the aft flow valve160(seeFIG. 9D), so that it is in the open position168(seeFIG. 9D), to release the trapped fluid189(seeFIG. 9D) from the fully inflated plurality of inflatable cascade members82(seeFIG. 9D), out through one or more pressure relief vents128(seeFIG. 9D) in cavity187(seeFIG. 9D) of the reduced length translating sleeve170a(seeFIG. 9D), and to move the plurality of inflatable cascade members82from the deployed inflated state86(seeFIG. 9D) back to the stowed deflated state84(seeFIG. 9A).

As shown inFIG. 12, the method280further comprises step292of moving concurrently the translating aft cascade support ring140(seeFIG. 9A), and the reduced length translating sleeve170a(seeFIG. 9A) and the one or more blocker doors48(seeFIG. 9A), from the deployed reverse thrust mode186(seeFIG. 9D) back to the stowed forward thrust mode181(seeFIG. 9A), and closing the aft flow valve160(seeFIG. 9A) back to the closed position166(seeFIG. 9A).

FIG. 13is an illustration of a flow diagram of an aircraft manufacturing and service method300.FIG. 14is an illustration of a functional block diagram of an aircraft320. Referring toFIGS. 13-14, examples of the disclosure may be described in the context of the aircraft manufacturing and service method300as shown inFIG. 13, and the aircraft320as shown inFIG. 14.

As shown inFIG. 13, during pre-production, exemplary aircraft manufacturing and service method300may include specification and design302of the aircraft320and material procurement304. As further shown inFIG. 13, during manufacturing, component and subassembly manufacturing306and system integration308of the aircraft320takes place. Thereafter, the aircraft320may go through certification and delivery310(seeFIG. 13) in order to be placed in service312(seeFIG. 13). While in service312(seeFIG. 13) by a customer, the aircraft320(seeFIG. 14) may be scheduled for routine maintenance and service314(seeFIG. 13) (which may also include modification, reconfiguration, refurbishment, and other suitable services).

As shown inFIG. 14, the aircraft320produced by the exemplary aircraft manufacturing and service method300may include an airframe322with a plurality of systems324and an interior326. Examples of the plurality of systems324may include one or more of a propulsion system328(seeFIG. 14), an electrical system330(seeFIG. 14), a hydraulic system332(seeFIG. 14), and an environmental system334(seeFIG. 14). Any number of other systems may be included. Although an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the automotive industry.

Methods and systems embodied herein may be employed during any one or more of the stages of the aircraft manufacturing and service method300(seeFIG. 13). For example, components or subassemblies corresponding to component and subassembly manufacturing306(seeFIG. 13) may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft320(seeFIG. 14) is in service312(seeFIG. 13). Also, one or more apparatus examples, method examples, or a combination thereof, may be utilized during component and subassembly manufacturing306(seeFIG. 13) and system integration308(seeFIG. 13), for example, by substantially expediting assembly of or reducing the cost of the aircraft320(seeFIG. 14). Similarly, one or more of apparatus examples, method examples, or a combination thereof, may be utilized while the aircraft320(seeFIG. 14) is in service312(seeFIG. 13), for example and without limitation, to maintenance and service314(seeFIG. 13).

Examples of the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), and the method280(seeFIG. 12) use the inflatable cascade assembly80(seeFIGS. 4, 9A-9D), use the translating aft cascade support ring140(seeFIGS. 4, 9A-9D) with the translating apparatus148(seeFIGS. 4, 9A-9D), such as the sliding apparatus148a(seeFIGS. 4, 9A-9D), and use the pressurized fluid supply system122(seeFIGS. 4, 9A-9D) with the pressurized fluid120(seeFIG. 4), such as the engine compressor bleed air120b(seeFIG. 4), or another suitable pressurized fluid120, and the supply ducts124(seeFIG. 9A), the inlet ducts126a(seeFIG. 9A), and the outlet ducts126b(seeFIG. 9A). Upon, or at, landing, the inflatable cascade assembly80(seeFIGS. 4, 9A-9D), which is in the stowed deflated state84(seeFIG. 6A), is inflated with the pressurized fluid120(seeFIGS. 4, 9C-9D), such as the engine compressor bleed air120b(seeFIG. 4), or another suitable pressurized fluid120, to form the shape of the fully deployed and inflated inflatable cascade assembly80in the deployed inflated state86(seeFIG. 9C). After deployment, the trapped fluid189(seeFIG. 9D), such as the trapped pressurized fluid, is extracted out of the inflatable cascade assembly80(seeFIGS. 4, 9D), so that the inflatable cascade assembly80may be stowed back into the original compact shape package inside the nacelle14(seeFIGS. 4, 9A).

In addition, examples of the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), and the method280(seeFIG. 12) allow for a cascade thrust reverser176(seeFIGS. 4, 9A-9D) design with an innovative thrust reverser hardware that utilizes an inflatable cascade assembly80(seeFIGS. 4, 9A-9D) to leverage the benefits of a shortened nacelle14a(seeFIGS. 4, 9A-9D), or compact nacelle. Such benefits include, but are not limited to, a reduced aerodynamic drag274(seeFIG. 4), such as a reduced nacelle external drag275(seeFIG. 4), an increased fan duct efficiency276(seeFIG. 4), an increased fan nozzle efficiency277(seeFIG. 4), and a reduced weight278(seeFIG. 4) and a reduced length279(seeFIG. 4) of the nacelle14(seeFIG. 4). The inflatable cascade system10(seeFIGS. 4, 9A-9D) efficiently uses the volumetric space for the thrust reverser hardware in the forward thrust nozzle configuration. The inflatable cascade hardware design enables a light-weight solution to the ultimate compact nacelle architecture.

Moreover, examples of the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), and the method280(seeFIG. 12) provide the shortened nacelle14a(seeFIGS. 4, 9A-9D), or compact nacelle, that enables favorable hard-point constraints at the translating aft cascade support ring140(seeFIGS. 4, 9A-9D) for the external nacelle aerodynamic line76(seeFIG. 3C) and the fan duct outer wall aerodynamic line78(seeFIG. 3C). In contrast to the known cascade-type thrust reverser system30(seeFIGS. 2, 3A, 3C), the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) enables positioning of the inflatable cascade member82(seeFIGS. 4, 6A) in the stowed deflated state84(seeFIG. 6A) in a compact volume, without affecting hard-point constraints to the external nacelle aerodynamic line76(seeFIG. 3C) and the fan duct outer wall aerodynamic line78(seeFIG. 3C). This ultimately helps to reduce the length and diameter of the nacelle14(seeFIGS. 4, 9A-9D). With relieved hard-point constraints from the translating aft cascade support ring140(seeFIGS. 4, 9A-9D), in contrast to the known cascade-type thrust reverser system30(seeFIGS. 2, 3A), a reduced length translating sleeve170a(seeFIG. 4) that is much shorter may be used and designed to reduce the nacelle external drag and the aerodynamic drag of the aircraft engine.

Accordingly, without compromising performance in the deployed reverse thrust mode186(seeFIG. 9C), the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) solves the problem of designing a compact thrust reverser hardware in a forward thrust mode and enables designing more efficient under-wing nacelle packages for the overall benefit of the air vehicle12(seeFIG. 1), such as the aircraft12a(seeFIG. 1). Further with the inflatable cascade assembly80(seeFIGS. 4, 9A) comprising the inflatable cascade member82(seeFIGS. 4, 9A), in the stowed deflated state84(seeFIG. 9A), the relaxed nozzle aerolines may have 0.2% to 0.4% specific fuel consumption (SFC) benefit, and the relaxed external nacelle aerolines may enable additional 0.1% to 0.15% external drag reduction. Moreover, the inflatable cascade system10(seeFIGS. 4, 9A-9D) allows for a shortened fan duct outer wall172b(seeFIGS. 9A-9D) that may be moved radially outward to open up the duct cross-sectional area which may help to reduce the fan duct cross-section Mach number and the skin/friction drag (Mach 2 effect). This may enable an increased fan nozzle efficiency277(seeFIG. 4), i.e. reduced specific fuel consumption (SFC).

In addition, the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) enables the inflatable cascade member82(seeFIGS. 4, 6A) in the stowed deflated state84(seeFIG. 6A) to have a stowed length85(seeFIG. 6A) that is much shorter than a deployed length87(seeFIG. 5A) of the inflatable cascade member82(seeFIGS. 4, 5A) in the deployed inflated state86(seeFIG. 5A). For example, the stowed length85(seeFIG. 6A) may be about 15% (fifteen percent) to about 25% (twenty-five percent) of the total length of the deployed length87(seeFIG. 5A) of the inflatable cascade member82(seeFIGS. 5A, 6A). For commercial aircraft engines, e.g., Boeing737,787,777, the length of a known solid material cascade assembly may be from about 20 (twenty) inches to about 30-35 (thirty to thirty-five) inches long. In contrast, the length of the inflatable cascade assembly80(seeFIGS. 4, 6A) comprising the inflatable cascade member82(seeFIGS. 4, 6A) in the stowed deflated state84(seeFIG. 6A) may be from about 3 (three) inches to about 5 (five) inches long. With the ability of the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) to be inflated and deflated, the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) is inflatable to assimilate known solid cascades. This is accomplished by inflating the inflatable cascade assembly80only when required for landing and when the cascade thrust reverser176(seeFIG. 4) is in operation, and stowing the inflatable cascade assembly80during regular or typical flight operation.

Further, examples of the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), and the method280(seeFIG. 12) provide for the translating aft cascade support ring140(seeFIGS. 4, 9A-9D) as a slider-style aft cascade support ring, which can slide or rail over the translating apparatus148(seeFIGS. 4, 9A-9D), such as the slider apparatus148a(seeFIGS. 4, 9A-9D) at the engine hinge and latch beams (not shown). This is in contrast to the known cascade-type thrust reverser system30(seeFIGS. 2, 3A, 3C), which has a solid cascade design, where the aft cascade support ring44(seeFIGS. 2, 3A, 3C) is fixed or immovable. For example, the known aft cascade support ring44(seeFIGS. 2, 3A) holds the cascade assembly42(seeFIGS. 2, 3A) in its position, remains in a fixed position, and is the constraining point to having a compact nacelle. With the translating aft cascade support ring140(seeFIGS. 4, 9A-9D) of the inflatable cascade system10(seeFIGS. 4, 9A-9D), the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) is translatable and is only required to be deployed for landing and when the cascade thrust reverser176(seeFIG. 4) is in operation, and may be stowed during regular or typical flight operation, to enable reduced aerodynamic drag274(seeFIG. 4) and increased fan nozzle efficiency277(seeFIG. 4).

Using the translating aft cascade support ring140(seeFIGS. 4, 9A-9D) eliminates or minimizes the hard-point constraints of the fixed aft cascade support ring44(seeFIG. 2), and by making the translating aft cascade support ring140(seeFIGS. 4, 9A-9Dmovable along the translating apparatus148(seeFIGS. 9A-9D), such as the slider apparatus148a(seeFIGS. 9A-9D), the known fan duct outer wall37b(seeFIGS. 9A-9D) can be shortened to the shortened fan duct outer wall172b(seeFIGS. 9A-9D), which, in turn, preferably makes the nacelle14(seeFIGS. 9A-9D) compact during flight operation, improving the efficiency of the engine16(seeFIGS. 9A-9D), and providing an increased fan nozzle efficiency277(seeFIG. 4) and an increased fan duct efficiency276(seeFIG. 4).

In addition, examples of the inflatable cascade system10(seeFIGS. 4, 9A-9D) with the inflatable cascade assembly80(seeFIGS. 4, 9A-9D) for the cascade thrust reverser system24(seeFIGS. 4, 9A-9D), such as the inflatable cascade thrust reverser system24a(seeFIGS. 4, 9A-9D), and the method280(seeFIG. 12) provide a safety feature or system with one or more safety devices190(seeFIGS. 4, 10). The safety devices190(seeFIG. 4) preferably comprise one or more pressure sensors190a(seeFIG. 4) configured to signal during the fully deployed position at reverse thrust stage184(seeFIGS. 9C, 10), one or more of, an air leakage191a(seeFIG. 4) in the inflatable cascade system10, a cascade breach191b(seeFIG. 4) of one or more of the plurality of inflatable cascade members82(seeFIG. 4), or another safety issue. The safety devices190(seeFIG. 4) may further comprise transducers, electrical signals, alarms, or other safety devices or safety notification devices. The one or more safety devices190(seeFIG. 4) preferably eliminate risk due to any air leakage191a(seeFIG. 4) or cascade breach191b(seeFIG. 4) or cascade puncture. Further, to prevent deflation because of air leakage191a(seeFIG. 4) during use, multiple internal tubes, such as separate tube elements130(seeFIG. 7A) or continuous segmented elements134(seeFIG. 7B) may be implemented in the second inflatable flexible side96(seeFIGS. 7A-7B) of the plurality of circumferential vanes92(seeFIGS. 7A-7B), so that if one internal tube leaks, then the other internal tubes keep the plurality of circumferential vanes92inflated. In addition, a plenum chamber136(seeFIG. 8A) comprising an orifice plate portion138(seeFIG. 8A), may be used to evenly distribute the pressurized fluid120(seeFIGS. 9A-9D) in the inflatable cascade assembly80(seeFIGS. 9A-9D) and the plurality of cascade vanes92(seeFIGS. 9A-9D). The extendable side supports118(seeFIGS. 5C, 6C) are used to elongate the plurality of circumferential vanes92(seeFIGS. 5C, 6C) and the plurality of inflatable support members102(seeFIGS. 5C, 6C) in a guided, straight manner similar to a manner of an accordion.

Many modifications and other examples of the disclosure will come to mind to one skilled in the art to which this disclosure pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. The examples described herein are meant to be illustrative and are not intended to be limiting or exhaustive. Although specific terms are employed herein, they are used in a generic and descriptive sense only and not for purposes of limitation.