Patent Description:
Turbojet engines for aircraft may frequently include variable area exhaust nozzles to accommodate subsonic, transonic, and supersonic speeds. Due to the different properties of exhaust gases as they flow through the nozzle at different speeds, there may be a need to vary the area of the nozzle at one or more locations within the nozzle in order to ensure proper and efficient turbojet operation over a range of aircraft flight conditions. In some cases, it may also be desirable to introduce ambient air to the nozzle exhaust within the nozzle to improve engine efficiency. What is needed are variable area nozzle assemblies which improve upon variable area nozzle assemblies conventionally known in the art.

Document <CIT> discloses a turbomachine ejector nozzle with a thrust reverser. Further document <CIT> discloses a variable geometry propulsion nozzle with a variable ejector.

According to an aspect of the present disclosure, a variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring disposed about a nozzle centerline. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. The variable area nozzle assembly further includes a nozzle disposed about the nozzle centerline and defining an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door disposed about the nozzle centerline. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions, in which the forward ejector door is positioned adjacent the aft ejector door, and respective open positions, in which the forward ejector door and the aft ejector door are spaced from one another to define a second portion of the ejector passage therebetween. The variable area nozzle assembly further includes a translating ejector sleeve mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position, in which the ejector passage is closed, and a second axial position, in which the ejector passage is open such that the ejector passage is configured to allow air flow therethrough from radially outside the fixed structure to radially inside the nozzle.

In a preferred embodiment, the translating ejector sleeve may be configured to effect pivoting of the forward ejector door and the aft ejector door such that axial translation of the translating ejector sleeve from the first axial position to the second axial position causes the forward ejector door and the aft ejector door to pivot from the respective closed positions to the respective open positions.

In a further preferred embodiment, an aft end of the aft ejector door may define an outlet cross-sectional area of the nozzle.

In a further preferred embodiment, the nozzle may further include a seal member positioned between the forward ejector door and the aft ejector door and configured to provide a seal between the forward ejector door and the aft ejector door when the forward ejector door and the aft ejector door are in the respective closed positions.

In a further preferred embodiment, the nozzle may further include an A8 door pivotably mounted to the first fixed ring. The A8 door may define a second surface portion of the inner radial exhaust flow path surface. The A8 door may be selectively pivotal relative to the nozzle centerline between a first A8 position defining a maximum area of a throat cross-sectional area of the nozzle and a second A8 position defining a minimum area of the throat cross-sectional area of the nozzle.

In a further preferred embodiment, the forward ejector door may be pivotably mounted to the A8 door.

In a further preferred embodiment, the variable area nozzle assembly may further include a first thrust reverser door and a second thrust reverser door. Each of the first thrust reverser door and the second thrust reverser door may be rotatably mounted to the fixed structure at a first thrust reverser door end.

In a further preferred embodiment, the aft ejector door may be pivotably mounted to the first thrust reverser door and the second thrust reverser door.

In a further preferred embodiment, a second thrust reverser door end of each of the first thrust reverser door and the second thrust reverser door may be configured to contact the second fixed ring when the first thrust reverser door and the second thrust reverser door are in respective stowed positions.

In a further preferred embodiment, the aft ejector door may be configured to rotate with the first thrust reverser door and the second thrust reverser door from the respective stowed positions of the first thrust reverser door and the second thrust reverser door to respective deployed positions of the first thrust reverser door and the second thrust reverser door.

According to another aspect of the present disclosure, a variable area nozzle assembly for a gas turbine engine includes a fixed structure disposed about a nozzle centerline and defining a first portion of an ejector passage extending from an outer radial side of the fixed structure to an inner radial side of the fixed structure. The variable area nozzle assembly further includes a nozzle disposed about the nozzle centerline and mounted to the fixed structure. The nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door disposed about the nozzle centerline and defining a first surface portion of the inner radial flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions in which the forward ejector door contacts the aft ejector door and respective open positions in which the forward ejector door and the aft ejector door are spaced from one another to define a second portion of the ejector passage therebetween. The variable area nozzle assembly further includes a translating ejector sleeve mounted within the fixed structure and configured to translate within the fixed structure between a first position, in which the translating ejector sleeve obstructs the ejector passage, and a second position, in which the translating ejector sleeve is configured to allow air flow through the ejector passage from radially outside the fixed structure to radially inside the nozzle.

In a preferred embodiment, the nozzle may further include an A8 door pivotably mounted to the fixed structure. The A8 door may define a second surface portion of the inner radial exhaust flow path surface. The A8 door may be selectively pivotal relative to the nozzle centerline between a first position defining a maximum area of a throat cross-sectional area of the nozzle and a second position defining a minimum area of the throat cross-sectional area of the nozzle.

In further preferred embodiment, the forward ejector door may be pivotably mounted to the A8 door at an axial location of the throat cross-sectional area.

In further preferred embodiment, the aft ejector door may be pivotably mounted to the first thrust reverser door and the second thrust reverser door.

In a further preferred embodiment, a second thrust reverser door end of each of the first thrust reverser door and the second thrust reverser door may be configured to contact the fixed structure when the first thrust reverser door and the second thrust reverser door are in respective stowed positions. The second thrust reverser door end of each of the first thrust reverser door and the second thrust reverser door may be configured to be spaced from the fixed structure when the first thrust reverser door and the second thrust reverser door are in the respective deployed positions.

According to another aspect of the present disclosure, a method for operating a variable area nozzle assembly for a gas turbine engine is provided. The method includes directing air through an ejector passage from radially outside a fixed structure to radially inside a nozzle by (<NUM>) axially translating a translating ejector sleeve within the fixed structure between a first axial position, in which the ejector passage is closed, and a second axial position, in which the ejector passage is open, and (<NUM>) pivoting a forward ejector door and an aft ejector door between a first ejector door position, in which the forward ejector door is positioned adjacent the aft ejector door, and a second ejector door position, in which the forward ejector door and the aft ejector door are spaced from one another.

In preferred embodiment, the translating ejector sleeve may be configured to effect pivoting of the first ejector door and the second ejector door such that the step of axially translating the translating ejector sleeve from the first position to the second position causes the forward ejector door and the aft ejector door to pivot from the first ejector door position to the second ejector door position.

In further preferred embodiment, the forward ejector door may be pivotably mounted to an A8 door of the nozzle which may be selectively pivotal relative to the nozzle centerline between a first A8 position defining a maximum area of a throat cross-sectional area of the nozzle and a second A8 position defining a minimum area of the throat cross-sectional area of the nozzle.

In further preferred embodiment, the aft ejector door may be pivotably mounted to a first thrust reverser door and a second thrust reverser door of the variable area nozzle assembly.

The present disclosure, and all its aspects, embodiments and advantages associated therewith will become more readily apparent in view of the detailed description provided below, including the accompanying drawings.

Referring to <FIG>, an exemplary gas turbine engine <NUM> capable of using aspects of the present disclosure is schematically illustrated. Although depicted as a turbojet gas turbine engine in the disclosed non-limiting embodiments, it should be understood that the concepts described herein are not limited to use with turbojets and may be applicable to other configurations of aircraft gas turbine engines as well including, but not limited to turboprop and turbofan gas turbine engines.

The gas turbine engine <NUM> generally includes an inlet structure <NUM> through which ambient air is directed into a core flow path <NUM> of the gas turbine engine <NUM>. The air within the core flow path <NUM> may be referred to as "core air. " The gas turbine engine <NUM> includes a compressor section <NUM>, for compressing the core air, and a combustor <NUM> wherein the compressed core air is mixed with fuel and ignited for generating combustion gases. The gas turbine engine <NUM> further includes a turbine section <NUM> for extracting energy from the combustion gases. The resultant combustion gases from the combustor <NUM> are expanded over the turbine section <NUM> and then exhausted via an exhaust section <NUM>, thereby providing thrust.

The compressor section <NUM> of the gas turbine engine <NUM> may include a low-pressure compressor 26A located upstream of a high-pressure compressor 26B. The turbine section <NUM> may include a high-pressure turbine 30B located upstream of a low-pressure turbine 30A. In one embodiment, the low-pressure compressor 26A may be connected to the low-pressure turbine 30A by a low-pressure shaft <NUM> and the high-pressure compressor 26B may be connected to the high-pressure turbine 30B by a high-pressure shaft <NUM>. The compressors 26A, 26B, the combustor <NUM>, and the turbines 30A, 30B may typically be concentric about a common axial centerline <NUM> (e.g., a rotational axis) of the gas turbine engine <NUM>.

The compressor section <NUM>, combustor <NUM>, and turbine section <NUM> are arranged sequentially along the axial centerline <NUM> within an engine housing <NUM>. This engine housing <NUM> includes an engine case <NUM> and a nacelle <NUM>. The engine case <NUM> houses one or more of the compressor section <NUM>, combustor <NUM>, and turbine section <NUM>, which may be collectively referred to as an "engine core. " The nacelle <NUM> houses and provides an aerodynamic cover for the engine case <NUM>. The engine housing <NUM> of <FIG> may also form the inlet structure <NUM> and at least a portion of a variable area nozzle assembly <NUM> for the exhaust section <NUM> of the gas turbine engine <NUM>.

Referring to <FIG>, aspects of the present disclosure include a variable area nozzle assembly <NUM> for the exhaust section <NUM> (see <FIG>). The variable area nozzle assembly <NUM> generally includes a fixed structure <NUM> of the gas turbine engine <NUM> which may be configured as or otherwise include, for example, portions of the engine housing <NUM> such as the engine case <NUM> and/or the nacelle <NUM>, and/or other suitable fixed structure of the gas turbine engine <NUM>. The fixed structure <NUM> radially surrounds an exhaust duct <NUM> generally disposed about a nozzle centerline <NUM> which may or may not be colinear with the axial centerline <NUM> of the gas turbine engine <NUM>. The variable area nozzle assembly <NUM> is configured to direct core gases along the flow path <NUM> from the turbine section <NUM> and/or bypass gases to a variable area nozzle <NUM> mounted to the fixed structure <NUM> and located at a downstream end of the exhaust section <NUM>. The nozzle <NUM> of <FIG> is configured as a convergent-divergent nozzle. However, the present disclosure is not limited to this particular nozzle configuration and aspects of the present disclosure may be applicable to other configurations of variable area nozzles as well.

The fixed structure <NUM> has an outer radial side <NUM> and an inner radial side <NUM> opposite the outer radial side <NUM>. The outer radial side <NUM> may form an exterior of the variable area nozzle assembly <NUM>. The fixed structure <NUM> includes a first fixed ring <NUM> and a second fixed ring <NUM> disposed about the nozzle centerline <NUM>. The first fixed ring <NUM> is axially spaced from the second fixed ring <NUM> to define a first portion of an ejector passage <NUM> therebetween and extending from the outer radial side <NUM> to the inner radial side <NUM>. The second fixed ring <NUM> may be mounted to the first fixed ring <NUM> by one or more side beams <NUM> extending aftward in a generally axial direction from the first fixed ring <NUM>. In some embodiments, for example referring to <FIG>, the side beams <NUM> may extend aftward past the second fixed ring <NUM>, and may be used to support one or more additional components of the variable area nozzle assembly <NUM>, as will be discussed in further detail.

Referring to <FIG>, in some embodiments, the nozzle <NUM> may include an A8 door <NUM> defining an upstream A8 axial portion of the nozzle <NUM> which may be a converging portion of the nozzle <NUM>. The A8 door <NUM> is disposed about the nozzle centerline <NUM> and defines a portion of an inner radial exhaust flow path surface <NUM> of the nozzle <NUM>. Additionally, the A8 door <NUM> may define a throat cross-sectional area <NUM> of the nozzle <NUM> at an axially aft (e.g., downstream) end of the A8 door <NUM>. In some embodiments, the A8 structure <NUM> may be fixedly mounted to the fixed structure <NUM> and may, therefore, define a fixed area of the throat cross-sectional area <NUM>. In some other embodiments, the A8 structure <NUM> may include a plurality of petals <NUM> (e.g., flaps) pivotably mounted to the first fixed ring <NUM> of the fixed structure <NUM>, relative to the nozzle centerline <NUM>, and configured to define a variable area of the throat cross-sectional area <NUM> (see <FIG>).

The petals <NUM> of the A8 door <NUM> of the nozzle <NUM> may be actuated to selectively vary the areas of the throat cross-sectional area <NUM>. As shown in <FIG>, for example, the A8 door <NUM> is in a radially innermost position such that the inner radial exhaust flow path surface <NUM> defines a minimum area of the throat cross-sectional area <NUM> (e.g., a minimum A8 position). For reference, an exemplary minimum A8 position of the A8 door <NUM> is represented in <FIG> by the dashed line <NUM>. As shown in <FIG>, for example, the A8 door <NUM> is in a radially outermost position such that the inner radial exhaust flow path surface <NUM> defines a maximum area of the throat cross-sectional area <NUM> (e.g., a maximum A8 position).

Referring to <FIG> and <FIG>, in some embodiments, the petals <NUM> of the A8 door <NUM> may be actuated by a sync ring <NUM>, as shown in <FIG>. The sync ring <NUM> may be disposed about the nozzle centerline <NUM> and mounted within the first fixed ring <NUM> of the fixed structure <NUM>. The sync ring <NUM> may be configured for translation (e.g., axial translation) within the first fixed ring <NUM> so as to move the petals <NUM> of the A8 door <NUM> between the minimum A8 position, the maximum A8 position, and a plurality of A8 positions therebetween. For example, the sync ring <NUM> may be connected to each of the petals <NUM> of the A8 door <NUM> by a linkage <NUM> which may extend through a respective slot (not shown) in the first fixed ring <NUM>.

Referring to <FIG>, the nozzle <NUM> includes a forward ejector door <NUM> and an aft ejector door <NUM> further defining the inner radial exhaust flow path surface <NUM> of the nozzle <NUM>. The ejector doors <NUM>, <NUM> define a downstream A9 axial portion of the nozzle <NUM> which may be a diverging portion of the nozzle <NUM>. The forward ejector door <NUM> includes a plurality of petals <NUM> circumferentially disposed about the nozzle centerline <NUM>. Similarly, the aft ejector door <NUM> includes a plurality of petals <NUM> circumferentially disposed about the nozzle centerline <NUM>. A downstream end <NUM> of the aft ejector door <NUM> defines an outlet cross-sectional area <NUM> of the nozzle <NUM>. In some embodiments, the A8 door <NUM>, the forward ejector door <NUM>, and the aft ejector door <NUM> may include a same number of petals <NUM>, <NUM>, <NUM>, whereas in some other embodiments, the number of petals <NUM>, <NUM>, <NUM> for each of the A8 door <NUM>, the forward ejector door <NUM>, and the aft ejector door <NUM> may be different from one another.

Each of the forward ejector door <NUM> and the aft ejector door <NUM> are pivotable between respective first positions (e.g., closed positions), in which the ejector doors <NUM>, <NUM> are disposed adjacent one another to define a continuous or substantially continuous inner radial exhaust flow path surface <NUM> of the nozzle <NUM> (see, e.g., <FIG>), and respective second positions (e.g., open positions), in which the ejector doors <NUM>, <NUM> are spaced from one another to define a second portion of the ejector passage <NUM> therebetween (see, e.g., <FIG>). In some embodiments, the nozzle <NUM> may include a circumferentially-extending seal member <NUM> mounted to one of the forward ejector door <NUM> or the aft ejector door <NUM> and configured to be positioned between the ejector doors <NUM>, <NUM> when the ejector doors <NUM>, <NUM> are in their respective closed positions to provide a seal between the ejector doors <NUM>, <NUM>.

In some embodiments including the A8 door <NUM>, an upstream end of the forward ejector door <NUM> may be pivotably mounted to a downstream end of the A8 door <NUM>. For example, petals <NUM> of the forward ejector door <NUM> may be pivotably mounted to petals <NUM> of the A8 door <NUM> at respective pivot joints <NUM>. As such, the forward ejector door <NUM> may be configured to pivot between the closed position and an open position in which an outer surface <NUM> of the forward ejector door <NUM> is positioned in contact with and/or adjacent an outer surface <NUM> of the A8 door <NUM>. In some other embodiments, such as those without an A8 door, the forward ejector door <NUM> may alternatively be pivotably mounted to the first fixed ring <NUM> of the fixed structure <NUM>.

In some embodiments, the downstream end <NUM> of the aft ejector door <NUM> may be pivotably mounted to the second fixed ring <NUM> of the fixed structure <NUM>. For example, petals <NUM> of the aft ejector door <NUM> may be pivotably mounted to second fixed ring <NUM>. As such, the aft ejector door <NUM> may be configured to pivot between the closed position, in which an upstream end <NUM> of the aft ejector door <NUM> may be positioned in contact with or proximate the forward ejector door <NUM> (see, e.g., <FIG>), and the open position, in which the upstream end <NUM> is displaced radially outward, relative to the position of the upstream end <NUM> with the aft ejector door <NUM> in the closed position, and in which the upstream end <NUM> may be disposed proximate or in contact with the second fixed ring <NUM> (see, e.g., <FIG>). In some embodiments, the aft ejector door <NUM> may be biased to the open position, for example, by one or more spring mechanisms <NUM> (e.g., a spring or spring cartridge) extending between the second fixed ring <NUM> and the aft ejector door <NUM>. In other embodiments, the spring mechanism <NUM> may include a torsion spring in contact with the second fixed ring <NUM> and the aft ejector door <NUM> along the pivot joint formed between the second fixed ring <NUM> and the aft ejector door <NUM> at the downstream end <NUM>.

Referring to <FIG> and <FIG>, the present disclosure variable area nozzle assembly <NUM> further includes a translating ejector sleeve <NUM> mounted to the fixed structure <NUM> and disposed about the nozzle centerline <NUM>. The translating ejector sleeve <NUM> is configured to axially translate within the fixed structure <NUM> between a first axial position in which the ejector passage <NUM> is closed (e.g., a closed position of the translating ejector sleeve <NUM>) and a second axial position in which the ejector passage <NUM> is open (e.g., an open position of the translating ejector sleeve <NUM>). In the closed position, the translating ejector sleeve <NUM> obstructs the ejector passage <NUM>, thereby preventing or substantially preventing the passage of air through the first portion of the ejector passage <NUM> between the first fixed ring <NUM> and the second fixed ring <NUM>, as shown in <FIG>. In the open position, the translating ejector sleeve <NUM> permits passage of air through the ejector passage <NUM> between the first fixed ring <NUM> and the second fixed ring <NUM>, as shown in <FIG>. The translating ejector sleeve <NUM> includes a sleeve body <NUM> having a forward axial end <NUM> and an aft axial end <NUM>. In the closed position, the aft axial end <NUM> may contact the second fixed ring <NUM>, whereas in the open position, the aft axial end <NUM> may be axially spaced from the second fixed ring <NUM>.

The translating ejector sleeve <NUM>, the forward ejector door <NUM>, the aft ejector door <NUM>, and the ejector passage <NUM> of the present disclosure variable area nozzle assembly <NUM> define, at least in part, an exhaust nozzle ejector <NUM> of the variable area nozzle assembly <NUM>. The exhaust nozzle ejector <NUM> is configured to selectively introduce airflow from outside the variable area nozzle assembly <NUM> (e.g., a source of relatively higher-pressure air) into a relatively low-pressure region within the interior of the nozzle <NUM> via the ejector passage <NUM>, for example, along the air flow path <NUM>. Introduction of relatively higher-pressure air into the nozzle <NUM> may be used to energize a slower radially outer stream of exhaust gases passing through the nozzle <NUM>, thereby enhancing nozzle <NUM> thrust. Accordingly, the exhaust nozzle ejector <NUM> of the present disclosure may be configured to operate so as to optimize engine performance during various flight conditions of an aircraft (e.g., subsonic or supersonic flight) while also providing a compact configuration within the variable area nozzle assembly <NUM>.

In some embodiments, the translating ejector sleeve <NUM> may include a plurality of projecting members <NUM> circumferentially spaced from one another about the nozzle centerline <NUM>. Each of the plurality of projecting members <NUM> may extend in an aftward axial direction from the aft axial end <NUM> of the sleeve body <NUM> to a distal end <NUM>. Each of the plurality of projecting members <NUM> may include a slot <NUM> extending radially therethrough. In some embodiments, the second fixed ring <NUM> may include a plurality of axial passages <NUM> circumferentially aligned with the plurality of projecting members <NUM>. The plurality of axial passages <NUM> may allow the respective plurality of projecting members <NUM> to axially translate within and through the second fixed ring <NUM>, as will be discussed in greater detail.

Referring to <FIG>, in some embodiments, the exhaust nozzle ejector <NUM> of the variable area nozzle assembly <NUM> may include an ejector actuation system <NUM>. The ejector actuation system <NUM> may include an array of linkages configured to selectively position the various components of the exhaust nozzle ejector <NUM> for open and closed conditions of the exhaust nozzle ejector <NUM>. Accordingly, the exemplary actuation system <NUM> shown in <FIG> includes a plurality of circumferentially spaced linkage assemblies <NUM>, one of which is shown in <FIG>. Each linkage assembly <NUM> includes a first ejector linkage <NUM>, a second ejector linkage <NUM>, a forward ejector door crank <NUM>, and an aft ejector door crank <NUM>. The first ejector linkage <NUM> includes a first end <NUM> rotatably mounted to a respective projecting member <NUM> of the translating ejector sleeve <NUM> within the slot <NUM> of the respective projecting member <NUM>. The axial length of the slot <NUM> may be sufficient to encompass the length of the first ejector linkage <NUM> therein. A second end <NUM> of the first ejector linkage <NUM> is rotatably mounted to a first end <NUM> of the forward ejector door crank <NUM>. A second end <NUM> of the forward ejector door crank <NUM> is rotatably mounted to the A8 door <NUM>, to a respective petal of the plurality of petals <NUM> for the A8 door <NUM> (as shown in <FIG>), or to the first fixed ring <NUM>. The second ejector linkage <NUM> includes a first end <NUM> rotatably mounted to an intermediate portion of the forward ejector door crank <NUM> between the first end <NUM> and the second end <NUM>. The second ejector linkage <NUM> includes a second end <NUM> rotatably mounted to a respective petal of the plurality of petals <NUM> for the forward ejector door <NUM>. In some embodiments, the forward ejector door <NUM> and/or the A8 door <NUM> may include a slot (not shown) in which the second ejector linkage <NUM> and/or the forward ejector door crank <NUM> may be at least partially disposed throughout the range of motion of the second ejector linkage <NUM> and/or the forward ejector door crank <NUM>. In some embodiments, the aft ejector door crank <NUM> may be rotatably mounted to the second fixed ring <NUM> at a pivot point <NUM> of the aft ejector door crank <NUM>. The aft ejector door crank <NUM> may include a first portion <NUM> generally extending in a direction away from the pivot point <NUM> to a first end <NUM>. The aft ejector door crank <NUM> may further include a second portion <NUM> generally extending in a direction away from the pivot point <NUM>, and transverse to the direction of the first portion <NUM>, to a second end <NUM>.

Actuation of the translating ejector sleeve <NUM> from the closed position (see <FIG>) to the open position (see <FIG>) effects movement of the forward ejector door <NUM> and the aft ejector door <NUM> to their respective open positions via the ejector actuation system <NUM>. As shown in <FIG>, with the translating ejector sleeve <NUM> in the open position, each of the projecting members <NUM> is disengaged from the first portion <NUM> of each aft ejector door crank <NUM>, thereby allowing spring force biasing of the aft ejector door <NUM> to the open position.

Similarly, actuation of the translating ejector sleeve <NUM> from the open position (see <FIG>) to the closed position (see <FIG>) effects movement of the forward ejector door <NUM> and the aft ejector door <NUM> to their respective closed positions via the ejector actuation system <NUM>. As shown in <FIG>, with the translating ejector sleeve <NUM> in the closed position, each of the projecting members <NUM> extends through a respective one of the passages <NUM> of the second fixed ring <NUM> to engage the first portion <NUM> of each aft ejector door crank <NUM>, thereby rotating the aft ejector door crank <NUM> so that the second portion <NUM> of the aft ejector door crank <NUM> forces the aft ejector door <NUM> to the closed position (e.g., against a spring force biasing the aft ejector door <NUM> to the open position).

Referring to <FIG>, in some embodiments, the variable area nozzle assembly <NUM> may include a thrust reverser system <NUM>. The thrust reverser system <NUM> may be configured, for example, as a post-exit thrust reverser as shown in <FIG>. The thrust reverser system <NUM> may include a first thrust reverser door <NUM> and a second thrust reverser door <NUM>. Each of the thrust reverser doors <NUM>, <NUM> extend between a forward end <NUM> and an aft end <NUM>. The thrust reverser doors <NUM>, <NUM> are pivotably mounted to the side beams <NUM> of the fixed structure <NUM> at or proximate the respective aft ends <NUM> of the thrust reverser doors <NUM>, <NUM> and at a position of the side beams <NUM> which is axially aft of the second fixed ring <NUM>. Accordingly, the thrust reverser doors <NUM>, <NUM> are configured to pivot between a stowed position (see <FIG> and <FIG>) and a deployed position (see <FIG> and <FIG>) in which the thrust reverser doors <NUM>, <NUM> are positioned axially aft of the nozzle <NUM> to block and/or deflect exhaust gases exiting the nozzle <NUM>. In the stowed position, the respective forward ends <NUM> of the thrust reverser doors <NUM>, <NUM> may contact or otherwise be positioned proximate the second fixed ring <NUM>. In some embodiments, the thrust reverser doors <NUM>, <NUM> may include a circumferentially-extending flange member <NUM> located along the respective forward ends <NUM> of the thrust reverser doors <NUM>, <NUM>. In the stowed position, the flange member <NUM> of the thrust reverser doors <NUM>, <NUM> may be mounted against the second fixed ring <NUM>.

As shown in <FIG>, the aft ejector door crank <NUM> of each linkage assembly <NUM> may be pivotably mounted to one of the thrust reverser doors <NUM>, <NUM>. For example, the aft ejector door crank <NUM> may be pivotably mounted to a portion of the flange member <NUM>. The flange member <NUM> may include a plurality of apertures <NUM> extending through the flange member <NUM>. With the thrust reverser doors <NUM>, <NUM> in the stowed position, the plurality of apertures <NUM> may be aligned with the plurality of axial passages <NUM> of the second fixed ring <NUM> as well as with respective aft ejector door cranks <NUM> of the plurality of linkage assemblies <NUM>. Accordingly, the plurality of projecting members <NUM> may axially translate within and through the axial passages <NUM> of the second fixed ring <NUM> and the plurality of apertures <NUM> aligned therewith, to engage or disengage the first portion <NUM> of each aft ejector door crank <NUM>, as previously discussed. Further still, with the translating ejector sleeve <NUM> in the closed position, the plurality of projecting members <NUM> may extend through respective apertures of the plurality of apertures <NUM> in the flange member <NUM>. In this state, the plurality of projecting members <NUM> may function as a locking device to securely retain the thrust reverser doors <NUM>, <NUM> in the stowed position (e.g., to prevent the thrust reverser doors <NUM>, <NUM> from pivoting from the stowed position toward the deployed position).

The downstream end <NUM> of the aft ejector door <NUM> may be pivotably mounted to the thrust reverser doors <NUM>, <NUM>. For example, each of the petals <NUM> of the aft ejector door <NUM> may be pivotably mounted to one of the thrust reverser doors <NUM>, <NUM>. As such, the aft ejector door <NUM> may be configured to pivot between the closed position, in which an upstream end <NUM> of the aft ejector door <NUM> may be positioned in contact with or proximate the forward ejector door <NUM> (see, e.g., <FIG>), and the open position, in which the upstream end <NUM> is displaced radially outward, relative to the position of the upstream end <NUM> with the aft ejector door <NUM> in the closed position, and in which the upstream end <NUM> may be disposed proximate or in contact with the flange member <NUM> (see, e.g., <FIG>). In some embodiments, the aft ejector door <NUM> may be biased to the open position, for example, by one or more springs (not shown). Because the aft ejector door <NUM> and aft ejector door cranks <NUM> are mounted to the thrust reverser doors <NUM>, <NUM>, the thrust reverser system <NUM>, including the combination of the thrust reverser doors <NUM>, <NUM>, aft ejector door <NUM>, and aft ejector door cranks <NUM>, may be configured to pivot between the stowed position and the deployed position of the thrust reverser doors <NUM>, <NUM> together, as shown in <FIG>.

The variable area nozzle assembly <NUM> may include actuators (e.g., hydraulic, pneumatic, electro-mechanical actuators) configured for moving various components of the variable area nozzle <NUM>, which are well known in the art. For the sake of clarity, these actuators have been omitted from the figures and description herein and the present disclosure is not limited to any particular actuator configuration for actuation of the sync ring <NUM>, the translating ejector sleeve <NUM>, and the thrust reverser doors <NUM>, <NUM>.

Claim 1:
A variable area nozzle assembly (<NUM>) for a gas turbine engine (<NUM>), the variable area nozzle assembly (<NUM>) comprising:
a fixed structure (<NUM>) comprising a first fixed ring (<NUM>) and a second fixed ring (<NUM>) disposed about a nozzle centerline (<NUM>), the second fixed ring (<NUM>) spaced axially aft from the first fixed ring (<NUM>) to define a first portion of an ejector passage (<NUM>) therebetween;
a nozzle (<NUM>) disposed about the nozzle centerline (<NUM>) and defining an inner radial exhaust flow path surface (<NUM>), the nozzle (<NUM>) comprising a forward ejector door (<NUM>) and an aft ejector door (<NUM>) disposed about the nozzle centerline (<NUM>), the forward ejector door (<NUM>) and the aft ejector door (<NUM>) defining a first surface portion of the inner radial exhaust flow path surface (<NUM>), each of the forward ejector door (<NUM>) and the aft ejector door (<NUM>) being pivotable between respective closed positions, in which the forward ejector door (<NUM>) is positioned adjacent the aft ejector door (<NUM>), and respective open positions, in which the forward ejector door (<NUM>) and the aft ejector door (<NUM>) are spaced from one another to define a second portion of the ejector passage (<NUM>) therebetween; and
a translating ejector sleeve (<NUM>) mounted within the fixed structure (<NUM>) and configured to axially translate within the fixed structure (<NUM>) between a first axial position, in which the ejector passage (<NUM>) is closed, and a second axial position, in which the ejector passage (<NUM>) is open such that the ejector passage (<NUM>) is configured to allow air flow therethrough from radially outside the fixed structure (<NUM>) to radially inside the nozzle (<NUM>).