Patent Description:
A propulsion system for an aircraft may include a thrust reverser system for providing reverse thrust. Various types and configurations of thrust reverser systems are known in the art. While these known thrust reverser systems have various advantages, there is still room in the art for an improved thrust reverser system.

<CIT> discloses a prior art assembly as set forth in the preamble of claim <NUM>.

<CIT> discloses a prior art thrust reverser system with hidden blocker doors.

<CIT> discloses a prior art translating cascade hidden blocker door thrust reverser.

According to an aspect of the present disclosure, an assembly is provided for an aircraft propulsion system as recited in claim <NUM>.

Features of embodiments of the disclosure are set forth in the dependent claims.

<FIG> illustrates an aircraft propulsion system <NUM> for an aircraft such as, but not limited to, a commercial airliner or a cargo plane. The propulsion system <NUM> includes a nacelle <NUM> and a gas turbine engine. This gas turbine engine may be configured as a turbofan engine as generally illustrated in <FIG>. Alternatively, the gas turbine engine may be configured as a turbojet engine or any other type of gas turbine engine capable of propelling the aircraft. The propulsion system <NUM> also includes a thrust reverser system <NUM> configured with the nacelle <NUM>; see also <FIG>.

The nacelle <NUM> of <FIG> substantially circumscribes and provides an aerodynamic covering for the gas turbine engine. Referring to <FIG>, the nacelle <NUM> in combination with at least a fan case <NUM> of the gas turbine engine also form a bypass flow path <NUM> within the aircraft propulsion system <NUM>. This bypass flow path <NUM> bypasses fan flow around a core of the gas turbine engine and is operable to route a majority (e.g., more than <NUM>%) of engine thrust out of the aircraft propulsion system <NUM> in, for example, the case of a turbofan engine configuration.

Referring to <FIG>, an outer structure <NUM> of the nacelle <NUM> extends axially along an axial centerline <NUM> of the aircraft propulsion system <NUM> (e.g., a rotational axis of the gas turbine engine) between a forward nacelle end <NUM> and an aft nacelle end <NUM>. The nacelle outer structure <NUM> includes a forward nacelle structure <NUM> and an aft nacelle structure <NUM>, which aft nacelle structure <NUM> is configured as or otherwise includes one or more translating sleeves <NUM>; e.g., thrust reverser sleeves.

The forward nacelle structure <NUM> includes an inlet structure <NUM> (e.g., module or cowl), one or more fan cowls <NUM> (one not visible in <FIG>) and a fixed / stationary support <NUM> (see <FIG>). The inlet structure <NUM> is disposed at the forward nacelle end <NUM>. The inlet structure <NUM> is configured to direct a stream of air through an inlet opening at the forward nacelle end <NUM> and into the gas turbine engine.

The first side fan cowl <NUM> is disposed on a first side of the aircraft propulsion system <NUM> (e.g., side visible in <FIG>). The second side fan cowl <NUM> is disposed on a second side of the aircraft propulsion system <NUM> (e.g., side not visible in <FIG>). Each fan cowl <NUM> is disposed axially between the inlet structure <NUM> and a respective one of the translating sleeves <NUM>. Each fan cowl <NUM>, for example, is disposed at an aft end <NUM> of the forward nacelle structure <NUM>, and extends forward to the inlet structure <NUM>. Each fan cowl <NUM> is generally axially aligned with a fan section of the gas turbine engine. Each fan cowl <NUM> is configured to provide an aerodynamic covering for the fan case <NUM>, which fan case <NUM> circumscribes the fan section and partially forms an outer peripheral boundary of the bypass flow path <NUM>; see <FIG>.

Referring to <FIG>, the stationary support <NUM> may be configured as or otherwise include a torque box for the thrust reverser system <NUM>. This stationary support <NUM> is attached to the fan case <NUM> at (e.g., on, adjacent or proximate) an aft end <NUM> of the fan case <NUM>. The stationary support <NUM> of <FIG> includes a ramp fairing structure <NUM> and a mounting structure <NUM>; e.g., a bulkhead structure.

The stationary support <NUM> extends circumferentially about the centerline <NUM>. The stationary support <NUM>, for example, may include a pair of partially-annular segments (e.g., halves) arranged on opposing sides of the propulsion system <NUM>. Alternatively, the stationary support <NUM> may have a substantially annular unitary body; e.g., may extend more than three-hundred and thirty degrees around the centerline <NUM>.

Referring to <FIG>, the first side translating sleeve <NUM> is disposed on the first side of the aircraft propulsion system <NUM> (e.g., side visible in <FIG>). The second side translating sleeve <NUM> is disposed on the second side of the aircraft propulsion system <NUM> (e.g., side not visible in <FIG>). Each translating sleeve <NUM> is disposed at the aft nacelle end <NUM>, and extends axially between a forward end <NUM> of the respective translating sleeve <NUM> and the aft nacelle end <NUM>. Each translating sleeve <NUM> is configured to further partially form the outer peripheral boundary of the bypass flow path <NUM> (see <FIG>), which bypass flow path <NUM> extends through the propulsion system <NUM> to a trailing edge of an engine exhaust nozzle <NUM>. The translating sleeves <NUM> may also form the nozzle <NUM> with an inner structure <NUM> of the nacelle <NUM> (often referred to as "an inner fixed structure"), which nacelle inner structure <NUM> houses the core of the gas turbine engine.

Referring to <FIG>, each translating sleeve <NUM> includes an inner sleeve panel <NUM> and an outer sleeve panel <NUM>. Each of these sleeve panels <NUM> and <NUM> extends circumferentially about the centerline <NUM> between opposing sleeve sides <NUM> and <NUM>. Each of the sleeve panels <NUM>, <NUM> extends axially along the centerline <NUM> from or about the forward end <NUM> to the aft end <NUM>. A forward end portion of the inner sleeve panel <NUM> is spaced radially inward of a forward end portion of the outer sleeve panel <NUM>. An aft end portion of the inner sleeve panel <NUM> meets an aft end portion of the outer sleeve panel <NUM> at the aft end <NUM>. The inner sleeve panel <NUM> and the outer sleeve panel <NUM> may thereby form an internal cavity <NUM> within the respective translating sleeve <NUM>. This cavity <NUM> extends radially within the respective translating sleeve <NUM> between (and to) the inner sleeve panel <NUM> and the outer sleeve panel <NUM>. The cavity <NUM> extends partially axially into the respective translating sleeve <NUM> from the forward end <NUM>. The cavity <NUM> may also extend circumferentially through (or alternatively within) the respective translating sleeve <NUM>.

Each translating sleeve <NUM> is configured with one or more sleeve sliders 82A and 82B (generally referred to as "<NUM>") and 84A and 84B (generally referred to as "<NUM>"). The translating sleeve <NUM> of <FIG>, for example, includes a pair of inner sleeve sliders <NUM> and a pair of outer sleeve sliders <NUM>. The inner sleeve sliders 82A and 82B are disposed on and attached to opposing sides <NUM> and <NUM> and in the cavity <NUM> of the inner sleeve panel <NUM>. The outer sleeve sliders 84A and 84B are disposed on an attached to opposing sides <NUM> and <NUM> and in the cavity <NUM> of the outer sleeve panel <NUM>. Referring to <FIG>, each of the sleeve sliders <NUM>, <NUM> is configured to mate with a respective sleeve track <NUM>, <NUM> connected to a fixed / stationary structure such as, but not limited to, a hinge beam <NUM> attached to a pylon structure or a latch beam <NUM> (e.g., at the lower side); see <FIG>. Each of the sleeve sliders <NUM>, <NUM> is also configured to move (e.g., translate) along the respective sleeve track <NUM>, <NUM>.

Referring to <FIG> and <FIG>, with foregoing arrangement, each translating sleeve <NUM> may move (e.g., translate) axially along the centerline <NUM> between a forward, sleeve stowed position (see <FIG>) and an aft, sleeve (e.g., fully) deployed position (see <FIG>). More particular, when being deployed, each translating sleeve <NUM> may translate in a first (e.g., aft) direction <NUM> along the centerline <NUM> from the sleeve stowed position (see <FIG>) to the sleeve deployed position (see <FIG>). In this deployed position of <FIG>, each translating sleeve <NUM> at least partially (or substantially completely) uncovers at least one of more other components of the thrust reverser system <NUM> such as, but not limited to, at least one respective fixed cascade structure <NUM>. The translating sleeve <NUM> also opens a respective thrust reverser passage <NUM> that extends radially through the nacelle outer structure <NUM>; see also <FIG>. When being stowed, the translating sleeve <NUM> may translate in a second (e.g., forward) direction <NUM> along the centerline <NUM> from the sleeve deployed position (see <FIG>) to the sleeve stowed position (see <FIG>), where the second direction <NUM> is opposite to the first direction <NUM> along the centerline <NUM>. In this stowed position of <FIG>, each translating sleeve <NUM> at least partially (or substantially completely) covers the at least one or more other components of the thrust reverser system <NUM> such as, but not limited to, the respective fixed cascade structure <NUM>. The translating sleeve <NUM> also closes (e.g., covers) the respective thrust reverser passage <NUM>.

Referring to <FIG>, the cavities <NUM> are provided with the nacelle <NUM> to house one or more components of the thrust reverser system <NUM> (when stowed) and, thereby, provide the bypass flow path <NUM> with fewer flow obstructions during typical forward flight propulsion system operation. By contrast, referring now to <FIG>, a typical prior art thrust reverser system <NUM> includes multiple components which can obstruct air flow through a bypass flow path <NUM> even when stowed. These components can include blocker doors <NUM>, where gaps (seams) between each blocker door <NUM> and adjacent elements can disrupt and turbulate boundary layer air flow. The component can also include drag links <NUM> and associated fittings <NUM>, which fittings <NUM> project into the bypass flow path <NUM> and to secure the drag links <NUM> to an inner fixed structure <NUM>, and which the drag links <NUM> extend radially through the bypass flow path <NUM> between the fittings <NUM> and the blocker doors <NUM>.

Referring again now to <FIG>, the thrust reverser system <NUM> of the present disclosure includes the stationary support <NUM>, the translating sleeves <NUM> and, associated with each translating sleeve <NUM>, a respective one of the cascade structures <NUM>, one or more blocker doors <NUM> and a blocker door actuation system <NUM>. To reduce flow obstructions to air flow within the bypass flow path <NUM>, the thrust reverser components (e.g., <NUM>, <NUM>, <NUM> and <NUM>) are arranged respectively within the cavities <NUM> when the translating sleeves <NUM> are stowed. In this manner, each inner sleeve panel <NUM> may have a substantially uninterrupted inner surface <NUM> that substantially axially abuts against the fan case <NUM> when stowed. Of course, an axial gap may exist between the fan case <NUM> and the inner surface <NUM> depending on the specific configuration of other nacelle structures such as the ramp fairing structure <NUM>.

The cascade structures <NUM> are arranged about the centerline <NUM>, for example, on opposing sides of the propulsion system <NUM>. For example, the first side cascade structure <NUM> is disposed on the first side of the aircraft propulsion system <NUM> (e.g., side visible in <FIG>). The second side cascade structure <NUM> is disposed on the second side of the aircraft propulsion system <NUM> (e.g., side not visible in <FIG>).

Each cascade structure <NUM> of <FIG> includes a cascade <NUM> and one or more cascade structure mounts <NUM> and <NUM>. The cascade <NUM> includes an axial array of turning vanes. The cascade <NUM> is connected to and extends axially between the cascade structure first (e.g., forward) mount <NUM> and the cascade structure second (e.g., aft) mount <NUM>. The cascade structure first mount <NUM> fixedly attaches the respective cascade structure <NUM> to the stationary support <NUM>. The respective cascade structure <NUM> thereby projects in the first direction <NUM> away from the stationary support <NUM> and across the respective thrust reverser passage <NUM> to the cascade structure second mount <NUM>.

Referring to <FIG>, the blocker doors <NUM> are arranged about the centerline <NUM> in, for example, a pair of partially annular arrays. These partially annular arrays of the blocker doors <NUM> may be arranged respectively on opposing sides of the propulsion system <NUM>, where each of the partially annular arrays is aligned with a respective one of the cascade structures <NUM>. Each of the blocker doors <NUM> extends circumferentially between opposing sides <NUM>. Each of the blocker doors <NUM> extends axially between a blocker door first (e.g., forward) end <NUM> and a blocker door second (e.g., aft) end <NUM>.

Each blocker door actuation system <NUM> of <FIG> includes one or more links <NUM> (e.g., linkages, link arms, rods, etc.), a translating frame <NUM> (e.g., a blocker door carriage) and one or more actuator systems <NUM> (e.g., reverse movement systems). Each link <NUM> extends longitudinally between a link first (e.g., forward) end <NUM> and a link second (e.g., aft) end <NUM>. Referring to <FIG> and <FIG>, each link <NUM> is moveably (e.g., pivotally) attached to the stationary support <NUM> at its first end <NUM> (or to the fixed cascade structure <NUM> or any other stationary structure) by, for example, a pivot (e.g., pin) connection. Each link <NUM> is moveably (e.g., pivotally) attached to a respective one of the blocker doors <NUM> at its second end <NUM> by, for example, a pivot (e.g., pin) connection. Each link <NUM> of <FIG> and <FIG>, for example, is pivotally attached to a mount <NUM> projecting radially outward from a panel of the blocker door <NUM>; see also <FIG>. Each mount <NUM> of <FIG> is positioned at an axial and/or laterally (e.g., circumferentially or tangentially) intermediate location along the blocker door <NUM>.

Referring to <FIG>, each translating frame <NUM> extends circumferentially about the centerline <NUM> between opposing frame sides <NUM> and <NUM>. Each translating frame <NUM> is configured with one of more frame sliders 134A and 134B (generally referred to as "<NUM>"). These frame sliders 134A and 134B are disposed on and connected to (e.g., formed integral with or otherwise attached to) the opposing sides <NUM> and <NUM> of the translating frame <NUM>. Referring to <FIG>, each frame slider <NUM> is configured to mate with a respective frame track 136A and 136B (generally referred to as "<NUM>") connected to the fixed / stationary structure such as, but not limited to, the hinge beam <NUM> (e.g., at the upper side) or the latch beam <NUM> (e.g., at the lower side). Each of the frame sliders <NUM> is also configured to move (e.g., translate) along the respective frame track <NUM>.

Referring to <FIG>, the blocker doors <NUM> are movably (e.g., pivotally) attached to the respective translating frame <NUM>. Each blocker door <NUM> of <FIG>, for example, includes one or more pivot attachments <NUM> at the second end <NUM>. These pivot attachments <NUM> pivotally attach that blocker door <NUM> to the respective translating frame <NUM> through, for example, a pivot (e.g., pin) connection.

The actuator systems <NUM> are arranged circumferentially about the centerline <NUM>. Referring to <FIG> and <FIG>, each actuator system <NUM> includes a fixed guide <NUM>, one or more lateral track sliders 142A and 142B (e.g., pins), an axial track slider <NUM> (e.g., pin), a latch <NUM>, one or more slider-to-slider (e.g., forward) links 148A and 148B and one or more slider-to-latch (e.g., aft) links 150A and 150B.

The fixed guide <NUM> includes one or more axial segments <NUM>-<NUM> (e.g., arms) and one or more lateral segments <NUM> and <NUM> (e.g., arms). The axial segments <NUM>-<NUM> of <FIG> and <FIG> are arranged in parallel with one another and, for example, the centerline <NUM> (not shown). Each axial segment <NUM>-<NUM> extends axially along the centerline <NUM> between an axial segment first (forward) end and an axial segment second (e.g., aft) end. Each axial segment <NUM>-<NUM> is fixedly mounted to the cascade structure second mount <NUM> of a respective one of the cascade structures <NUM> at its first end. Each axial segment <NUM>-<NUM> projects axially in the first direction <NUM> away from the cascade structure <NUM> and along the centerline <NUM> to its second end. The lateral intermediate axial segment <NUM> is positioned laterally (e.g., centered) between the lateral side axial segments <NUM> and <NUM>. This lateral intermediate axial segment <NUM> is configured with an axial track <NUM>; e.g., an axially elongated slot.

The first side lateral segment <NUM> is connected to (e.g., formed integrally with) and extends laterally between the first lateral side axial segment <NUM> and the lateral intermediate segment <NUM>. This first side lateral segment <NUM> is arranged at the axial segment second ends. The first side lateral segment <NUM> is configured with a first lateral track <NUM>; e.g., a laterally elongated slot. A centerline of the first lateral track <NUM> of <FIG> and <FIG> is arranged perpendicular to a centerline of the axial track <NUM>.

The second side lateral segment <NUM> is connected to (e.g., formed integrally with) and extends laterally between the second lateral side axial segment <NUM> and the lateral intermediate segment <NUM>. This second side lateral segment <NUM> is arranged at the axial segment second ends. The second side lateral segment <NUM> is configured with a second lateral track <NUM>; e.g., a laterally elongated slot. A centerline of the second lateral track <NUM> of <FIG> and <FIG> is arranged perpendicular to the centerline of the axial track <NUM>. The centerline of the second lateral track <NUM> of <FIG> and <FIG> is arranged is parallel with and may be coaxial with the centerline of the first lateral track <NUM>.

The first lateral track slider 142A is mated with the first lateral track <NUM>. The first lateral track slider 142A is configured to translate laterally (e.g., circumferentially, tangentially, in a direction perpendicular to the centerline <NUM> in a plane that is radially spaced from and parallel with the centerline <NUM>, etc.) along the first lateral track <NUM>.

The second lateral track slider 142B is mated with the second lateral track <NUM>. The second lateral track slider 142B is configured to translate laterally (e.g., circumferentially, tangentially, in a direction perpendicular to the centerline <NUM> in a plane that is radially spaced from and parallel with the centerline <NUM>, etc.) along the second lateral track <NUM>.

The axial track slider <NUM> is mated with the axial track <NUM>. The axial track slider <NUM> is configured to translate axially along the axial track <NUM> and the centerline <NUM>. The axial track slider <NUM> is also coupled with (e.g., pinned to) the translating frame <NUM>; e.g., see <FIG>.

The latch <NUM> is configured to temporarily couple the blocker doors <NUM> to a respective one of the translating sleeves <NUM> as described below in further detail; e.g., see <FIG>. The latch <NUM> of <FIG> and <FIG> includes a thrust rod <NUM>, a latch (e.g., pivot) attachment <NUM>, a yoke <NUM> and a cam <NUM>.

The thrust rod <NUM> extends axially between a thrust rod first (e.g., forward) end a thrust rod second (e.g., aft) end. The thrust rod <NUM> is slidably attached to the fixed guide <NUM> and, more particularly, its intermediate support segment <NUM> by one or more flanges <NUM> located proximate or at the axial segment aft end. The thrust rod <NUM> of <FIG>, for example, extends axially through apertures in the flanges <NUM>.

The latch attachment <NUM> is configured as a pin connection (e.g., a pin). The latch attachment <NUM> is located at the thrust rod second end. More particularly, the latch attachment <NUM> is connected to and projects radially inward from the thrust rod <NUM>.

Referring to <FIG>, the yoke <NUM> has a generally U-shaped geometry. The yoke <NUM> of <FIG>, for example, is configured with a first side foot 178A and a second side foot 178B. These feet 178A and 178B (generally referred to as "<NUM>") are laterally spaced from one another and connected to the thrust rod <NUM> at the first end.

The cam <NUM> is arranged in a channel formed laterally between the first side foot 178A and the second side foot 178B. The cam <NUM> of <FIG> is moveably (e.g., pivotally) connected to the yoke <NUM> by a pin <NUM>. Referring to <FIG>, the cam <NUM> may also be spring loaded by one or more coil springs <NUM> wrapped around the pin <NUM>. These springs <NUM> may bias the cam <NUM> in a closed position as shown in <FIG>.

Referring to <FIG>, each slider-to-slider link <NUM> extends between a link first (e.g., forward) end and a link second (e.g., aft) end. Each slider-to-slider link extends between and is pivotally connected to the axial track slider <NUM> and a respective one of the lateral track sliders <NUM>. More particularly, the first slider-to-slider link 148A is pivotally connected to the axial track slider <NUM> at its link first end. The first slider-to-slider link 148A is pivotally connected to the first lateral track slider 142A at its second end. The second slider-to-slider link 148B is pivotally connected to the axial track slider <NUM> at its link first end. The second slider-to-slider link 148B is pivotally connected to the second lateral track slider 142B at its second end.

Each slider-to-latch link <NUM> extends between a link first (e.g., forward) end and a link second (e.g., aft) end. Each slider-to-latch link <NUM> extends between and is pivotally connected to the latch <NUM> and a respective one of the lateral track sliders <NUM>. More particularly, the first slider-to-latch link 150A is pivotally connected to the first lateral track slider 142A at its first end. The first slider-to-latch link 150A is pivotally connected to the latch attachment <NUM> at its second end. The second slider-to-latch link 150B is pivotally connected to the second lateral track slider 142B at its first end. The second slider-to-latch link 150B is pivotally connected to the latch attachment <NUM> at its second end.

With the arrangement of the links <NUM> and <NUM> described above and illustrated in <FIG> and <FIG>, each actuator system <NUM> is configured with a scissor-type linkage; e.g., an inverse scissor linkage. The present disclosure, however, is not limited to such an exemplary actuator system configuration.

During propulsion system <NUM> operation, the thrust reverser system <NUM> may be actuated and deployed as illustrated by the sequence of <FIG>. At the beginning (e.g., start) of this deployment sequence (see <FIG>), the thrust reverser components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> are within the cavities <NUM> as described above. More particularly, the components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> are substantially completely housed within the cavities <NUM> and, thus, are outside (e.g., radially outboard) of the bypass flow path <NUM>.

During a first (e.g., initial) portion of the deployment sequence (see <FIG>), each translating sleeve <NUM> moves substantially axially in the first direction <NUM> away from the forward nacelle structure <NUM> (see <FIG>) and the stationary support <NUM>. More particularly, each translating sleeve <NUM> translates axially aft from the sleeve stowed position (see <FIG>) to a sleeve intermediate position (see <FIG>), which sleeve intermediate position is between the sleeve stowed position (see <FIG>) and the sleeve deployed position (see <FIG>). During this first portion of the translating sleeve <NUM> stroke, the other components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> of the thrust reverser system <NUM> may remain stationary. Thus, each translating sleeve <NUM> moves axially relative to the other components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> of the thrust reverser system <NUM>. This relative movement results in one or more of the components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> being at least partially axially withdrawn from the cavities <NUM>. However, because the components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> themselves are not moving, the components <NUM>, <NUM>, <NUM>, <NUM> and <NUM> may remain outside (e.g., radially outboard) of the bypass flow path <NUM>.

Referring to <FIG>, at the intermediate position, a trigger <NUM> mounted to or included with the translating sleeve <NUM> temporarily engages (e.g., axially contacts) a respective one of the yokes <NUM>. More particularly, a pair of deployment feet <NUM> of the trigger <NUM> (one visible in <FIG>) respectively engage the yoke feet <NUM>. As a result, as each translating sleeve <NUM> continues to move in the first direction <NUM> from the intermediate position (see <FIG>) to the deployed position (see <FIG>), the trigger <NUM> pushes against the yoke <NUM> and moves the yoke <NUM> in the first direction <NUM> as shown in the sequence of <FIG>. This first direction <NUM> movement of the yoke <NUM> in turn causes the links <NUM> and <NUM> to laterally close as shown in the sequence of <FIG>. The lateral closing of the links <NUM> and <NUM> in turn causes the axial track slider <NUM> to move in the second (e.g., forward) direction and push the translating frame <NUM> (see <FIG>) and the pivot attachments <NUM> in the second direction <NUM>. Each pivot attachment <NUM> thereby moves from a first (e.g., aft) location (see <FIG>) to a second (e.g., forward) location (see <FIG>) and thereby deploy the blocker doors <NUM> radially inward into the bypass flow path <NUM> and towards the centerline <NUM> (not shown); e.g., movement of the blocker doors <NUM> is controlled by the respective links <NUM>. Thus, as each translating sleeve <NUM> continues to move in the first direction <NUM> from the sleeve intermediate position (see <FIG>) to the sleeve deployed position (see <FIG>), the blocker door actuation system <NUM> causes each blocker door <NUM> to move from its stowed position (see <FIG>) to its (e.g., fully) deployed position (see <FIG>).

When the blocker doors <NUM> are in their stowed positions (see <FIG>), each cam <NUM> is seated in a recess <NUM> of the respective fixed guide <NUM> and its intermediate support segment <NUM> as shown in <FIG> with the help of spring <NUM>. While the cam <NUM> is seated within the recess <NUM> (e.g., stowed), a retraction foot <NUM> of the trigger <NUM> is able to pass laterally in between the yoke feet <NUM> and axially over the cam <NUM>. However, as the trigger <NUM> pushes the yoke <NUM> in the first direction <NUM> (see sequence of <FIG>), the cam <NUM> rotates radially outward into a deployed position. More particularly, as the yoke <NUM> moves in the first direction <NUM>, the cam <NUM> slides along a ramp <NUM> on the respective intermediate support segment <NUM> which causes the cam <NUM> to rotate radially outward until, for example, the cam <NUM> abuts against and axially engages (e.g., contacts) the retraction foot <NUM>. In this position, the cam <NUM> is operable to facilitate stowage of the blocker doors <NUM> when the respective translating sleeve <NUM> moves in the second direction <NUM> from the sleeve deployed position (see <FIG>) to the sleeve intermediate position (see <FIG>). In other words, the retraction foot <NUM> pushes axially against the cam <NUM> so as to cause the blocker door actuation system <NUM> to reverse its operation and thereby move the blocker doors <NUM> from their deployed position (see <FIG>) to their stowed position (see <FIG>).

Referring again to <FIG>, when the blocker doors <NUM> are in their stowed positions, the lateral track sliders <NUM> are separated by a first lateral distance <NUM> and the axial track slider <NUM> and the attachment <NUM> are separated by a first axial distance <NUM>. Referring to <FIG>, when the blocker doors <NUM> are in their deployed positions, the track sliders <NUM> are separated by a second lateral distance <NUM> and the axial track slider <NUM> and the attachment <NUM> are separated by a second axial distance <NUM>. The first lateral distance <NUM> is greater than the second lateral distance <NUM>. The first axial distance <NUM> is less than the second axial distance <NUM>.

In some embodiments, referring to <FIG>, a spring element <NUM> (e.g., a coil spring) may be configured with the latch <NUM> to bias the latch <NUM> in its stowed / forward position. This spring element <NUM> may extend between and be attached to the attachment <NUM> and the second mount <NUM>.

Claim 1:
An assembly for an aircraft propulsion system (<NUM>), comprising:
a thrust reverser system (<NUM>) including a sleeve (<NUM>) and a blocker door (<NUM>);
the sleeve (<NUM>) configured to translate in an aft direction (<NUM>) along a centerline (<NUM>) from a sleeve stowed position to a sleeve deployed position;
the blocker door (<NUM>) configured to move between a blocker door stowed position and a blocker door deployed position, the blocker door (<NUM>) disposed within a cavity (<NUM>) of the sleeve (<NUM>) when the sleeve (<NUM>) is in the sleeve stowed position and the blocker door (<NUM>) is in the blocker door stowed position, and the blocker door (<NUM>) projecting in a radial inward direction away from the sleeve (<NUM>) towards the centerline (<NUM>) when the sleeve (<NUM>) is in the sleeve deployed position and the blocker door (<NUM>) is in the blocker door deployed position; and
the blocker door (<NUM>) comprising a pivot attachment (<NUM>) fixed at an end (<NUM>) of the blocker door (<NUM>), the pivot attachment (<NUM>) configured to move in a forward direction (<NUM>) from a first location to a second location,
wherein the thrust reverser system (<NUM>) includes a fixed cascade structure (<NUM>) disposed within the cavity (<NUM>) of the sleeve (<NUM>) when the sleeve (<NUM>) is in the sleeve stowed position;
characterised in that the assembly comprises:
a fixed structure (<NUM>; <NUM>), wherein the fixed structure (<NUM>; <NUM>) comprises a frame track (136A; 136B); and
a frame (<NUM>) extending circumferentially about the centerline (<NUM>) to a frame side (<NUM>; <NUM>), the frame (<NUM>) comprising a frame slider (134A; 134B) at the frame side (<NUM>; <NUM>), and the frame slider (134A; 134B) configured to translate along the frame track (136A; 136B) as the blocker door (<NUM>) moves towards and away from the blocker door deployed position; and
the pivot attachment (<NUM>) pivotally attaches the blocker door (<NUM>) to the frame (<NUM>).