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.

Prior art includes <CIT>, <CIT>, <CIT> and <CIT>.

According to an aspect of the present invention, an assembly is provided for an aircraft propulsion system as claimed in claim <NUM>. Various embodiments of the invention are set out in the claims dependent thereon.

<FIG> illustrates an aircraft propulsion system <NUM> for an aircraft such as, but not limited to, a commercial airliner or a cargo plane. The aircraft propulsion system <NUM> includes a nacelle <NUM> and a gas turbine engine. This gas turbine engine may be configured as a high-bypass turbofan engine. 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 during flight. The aircraft propulsion system <NUM> also includes a thrust reverser system <NUM> configured with the nacelle <NUM>; see also <FIG>.

The nacelle <NUM> is configured to house and provide an aerodynamic cover for the gas turbine engine. An outer structure <NUM> of the nacelle <NUM> extends axially along an axial centerline <NUM> (e.g., a centerline of the aircraft propulsion system <NUM>, the nacelle <NUM> and/or the gas turbine engine) between a nacelle forward end <NUM> and a nacelle aft end <NUM>. The nacelle outer structure <NUM> of <FIG> includes a nacelle inlet structure <NUM>, one or more fan cowls <NUM> (one such cowl visible in <FIG>) and a nacelle aft structure <NUM>, which is configured as part of or includes the thrust reverser system <NUM> (see also <FIG>).

The inlet structure <NUM> is disposed at the nacelle forward end <NUM>. The inlet structure <NUM> is configured to direct a stream of air through an inlet opening <NUM> at the nacelle forward end <NUM> and into a fan section <NUM> of the gas turbine engine.

The fan cowls <NUM> are disposed axially between the inlet structure <NUM> and the nacelle aft structure <NUM>. Each fan cowl <NUM> of <FIG>, for example, is disposed next to and abutted axially against a forward end <NUM> of the nacelle aft structure <NUM>. Each of the fan cowls <NUM> is generally axially aligned with the fan section <NUM> of the gas turbine engine. The fan cowls <NUM> are configured to provide an aerodynamic covering for a fan case <NUM>.

The nacelle aft structure <NUM> includes an outer fixed structure <NUM> and a translating sleeve <NUM>. The outer fixed structure <NUM> is disposed at the aft structure forward end <NUM>. The outer fixed structure <NUM> of <FIG>, for example, is arranged axially between the fan cowls <NUM> and the translating sleeve <NUM>.

The translating sleeve <NUM> is disposed at the nacelle aft end <NUM>. This translating sleeve <NUM> extends axially along the axial centerline <NUM> between a forward end <NUM> of the translating sleeve <NUM> and the nacelle aft end <NUM>. The translating sleeve <NUM> of <FIG> includes a pair of sleeve segments <NUM> (e.g., halves) arranged on opposing sides of the aircraft propulsion system <NUM> (one such sleeve segment <NUM> visible in <FIG>). The present disclosure, however, is not limited to such an exemplary translating sleeve configuration. For example, the translating sleeve <NUM> may alternatively have a substantially tubular body. For example, the translating sleeve <NUM> may extend more than three-hundred and thirty degrees (<NUM>°) around the axial centerline <NUM>.

Referring to <FIG>, the translating sleeve <NUM> is an axially translatable structure. Each translating sleeve segment <NUM>, for example, may be slidably connected to one or more stationary structures (e.g., a pylon and a lower bifurcation) through one or more respective track assemblies <NUM>. Each track assembly <NUM> may include a rail mated with a track beam; however, the present disclosure is not limited to the foregoing exemplary sliding connection configuration. The translating sleeve <NUM> and its sleeve segments <NUM> are thereby configured to translate axially along the axial centerline <NUM> between a forward, stowed position (see <FIG>) and an aft, deployed position (see <FIG>). In the sleeve stowed position of <FIG>, the sleeve forward end <NUM> is disposed axially next to and abutted axially against an aft end <NUM> of the outer fixed structure <NUM>. In the sleeve deployed position of <FIG>, the sleeve forward end <NUM> is spaced / separated from the outer fixed structure aft end <NUM> by an axial distance. The translating sleeve <NUM> and its sleeve segments <NUM> may thereby open up / uncover a flow passage <NUM> through the thrust reverser system <NUM>.

The thrust reverser system <NUM> of <FIG> may include one or more sections <NUM> (one such thrust reverser sections <NUM> visible in <FIG>), where the thrust reverser sections <NUM> may be disposed on opposing sides of the aircraft propulsion system <NUM>. Referring to <FIG>, the thrust reverser system <NUM> and each of its thrust reverser sections <NUM> may include a segment <NUM> of the outer fixed structure <NUM>, a fan ramp fairing <NUM> (also sometimes referred to as a bullnose ramp) and a segment of the translating sleeve <NUM> (e.g., one of the sleeve segments <NUM>). The thrust reverser system <NUM> and each of its thrust reverser sections <NUM> also includes one or more door assemblies <NUM>; see also <FIG>.

The outer fixed structure <NUM> and its segment <NUM> of <FIG> are configured as a support structure (e.g., a torque box) for the thrust reverser system <NUM>. The outer fixed structure <NUM> and its segment <NUM> of <FIG> have a channeled (e.g., U-shaped or C-shaped) sectional geometry, which channel sectional geometry extends circumferentially about the axial centerline <NUM>. The outer fixed structure <NUM> and its segment <NUM> of <FIG>, for example, include a structure outer wall <NUM>, a structure inner wall <NUM> and a structure bulkhead wall <NUM>. These outer fixed structure members <NUM>, <NUM> and <NUM> may collectively form an internal channel <NUM> within the outer fixed structure <NUM> and its segment <NUM>.

The structure outer wall <NUM> may partially form an external peripheral boundary of the aircraft propulsion system <NUM> and its nacelle <NUM>. The structure outer wall <NUM> of <FIG>, for example, forms a segment <NUM> of an exterior aerodynamic flow surface <NUM> of the nacelle <NUM>. This flow surface segment <NUM> may be flush with exterior surface segments <NUM> and <NUM> of a respective fan cowl <NUM> and the translating sleeve <NUM> and a respective one of its sleeve segments <NUM>.

The structure inner wall <NUM> is disposed radially within the structure outer wall <NUM>. The structure inner wall <NUM> is disposed radially outboard of and axially overlaps the fan case <NUM>.

The structure bulkhead wall <NUM> may be disposed at a forward end of the outer fixed structure <NUM>. The structure bulkhead wall <NUM> extends radially between and is connected to the structure outer wall <NUM> and the structure inner wall <NUM>.

The structure channel <NUM> extends axially along the axial centerline <NUM> (e.g., partially) into the outer fixed structure <NUM> and its segment <NUM> from the structure aft end <NUM> to the structure bulkhead wall <NUM>. The structure channel <NUM> extends radially within the outer fixed structure <NUM> and its segment <NUM> between and to the structure outer wall <NUM> and the structure inner wall <NUM>. The structure channel <NUM> extends circumferentially within (or into or through) the outer fixed structure <NUM> and its segment <NUM> circumferentially about the axial centerline <NUM>.

The ramp fairing <NUM> is connected to the structure inner wall <NUM>, for example, through a frame <NUM>. The ramp fairing <NUM> is located at (e.g., on, adjacent or proximate) the structure aft end <NUM>. Referring to <FIG>, the ramp fairing <NUM> is configured to provide a (e.g., smooth and/or aerodynamic) transition from a forward portion of a bypass flowpath <NUM> to the respective thrust reverser flow passage <NUM> when the thrust reverser system <NUM> is in its deployed configuration.

The translating sleeve <NUM> and its sleeve segment <NUM> of <FIG> includes a sleeve outer panel <NUM> and a sleeve inner panel <NUM>. The sleeve outer panel <NUM> is disposed radially outboard of the sleeve inner panel <NUM>. The sleeve outer panel <NUM> circumferentially and axially overlaps the sleeve inner panel <NUM>. The sleeve outer panel <NUM> is radially spaced (e.g., separated) from the sleeve inner panel <NUM> at the sleeve forward end <NUM>. The sleeve outer panel <NUM>, however, may meet and/or be connected to the sleeve inner panel <NUM> at or about the nacelle aft end <NUM>. The sleeve outer panel <NUM> and the sleeve inner panel <NUM> may thereby form an internal channel <NUM> within the translating sleeve <NUM> and its sleeve segment <NUM>.

The sleeve channel <NUM> extends axially along the axial centerline <NUM> (e.g., partially) into the translating sleeve <NUM> and its sleeve segment <NUM> from the sleeve forward end <NUM> to a connection (e.g., an interface, a joint, etc.) between the sleeve outer panel <NUM> and the sleeve inner panel <NUM>. The sleeve channel <NUM> extends radially within the translating sleeve <NUM> and its sleeve segment <NUM> between and to the sleeve inner panel <NUM> and the sleeve outer panel <NUM>. The sleeve channel <NUM> extends circumferentially within (or into or through) the translating sleeve <NUM> and its sleeve segment <NUM> circumferentially about the axial centerline <NUM>.

Referring to <FIG>, the door assemblies <NUM> are distributed circumferentially about the axial centerline <NUM> in, for example, an arcuate or generally annular array. Referring to <FIG> and <FIG>, each of the door assemblies <NUM> includes a thrust reverser (TR) turning door <NUM>, a thrust reverser (TR) blocker door <NUM>, a turning door actuation linkage <NUM> (e.g., an inter-door linkage) and a blocker door actuation linkage <NUM> (e.g., a drag linkage).

Referring to <FIG>, the TR turning door <NUM> includes a turning door panel <NUM>, one or more turning door pivot mounts <NUM> (one such mount visible in <FIG>) and at least one turning door linkage mount <NUM>. The turning door panel <NUM> extends longitudinally (e.g., axially along the axial centerline <NUM> when the TR turning door <NUM> is stowed; e.g., see <FIG>) between and to a first end <NUM> of the turning door panel <NUM> and a second end <NUM> of the turning door panel <NUM>. This turning door first end <NUM> may be an axially forward end of the turning door panel <NUM> when the TR turning door <NUM> is in a stowed position (e.g., see <FIG>) and/or a deployed position (e.g., see <FIG>). The turning door first end <NUM> may also be a radial outer end of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door deployed position (e.g., see <FIG>). By contrast, the turning door second end <NUM> may be an axially aft end of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door stowed position (e.g., see <FIG>) and/or the turning door deployed position (e.g., see <FIG>). The turning door second end <NUM> may also be a radial inner end of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door deployed position (e.g., see <FIG>).

The turning door panel <NUM> extends laterally (e.g., circumferentially or tangentially) between and to opposing sides <NUM> of the TR turning door <NUM>. The turning door panel <NUM> extends vertically (e.g., radially when the TR turning door <NUM> is stowed; e.g., see <FIG>) between and to a front side <NUM> of the turning door panel <NUM> and a back side <NUM> of the turning door panel <NUM>. The turning door front side <NUM> may be a radial inner side of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door stowed position (e.g., see <FIG>), and the turning door front side <NUM> may be an axially forward side of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door deployed position (e.g., see <FIG>). By contrast, the turning door back side <NUM> may be a radial outer side of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door stowed position (e.g., see <FIG>), and the turning door back side <NUM> may be an axially aft side of the turning door panel <NUM> when the TR turning door <NUM> is in the turning door deployed position (e.g., see <FIG>).

Each of the turning door pivot mounts <NUM> is connected (e.g., fixedly secured) to the turning door panel <NUM> at its turning door back side <NUM>. Each of the turning door pivot mounts <NUM> projects out from the turning door panel <NUM> and its turning door back side <NUM> to a distal end of the respective turning door pivot mount <NUM>. Each of the turning door pivot mounts <NUM> of <FIG> is configured as a mounting tab.

The turning door linkage mount <NUM> is fixedly connected (e.g., fixedly secured) to the turning door panel <NUM> at its turning door back side <NUM>. The turning door linkage mount <NUM> projects out from the turning door panel <NUM> and its turning door back side <NUM> to a distal end of the turning door linkage mount <NUM>. The turning door linkage mount <NUM> of <FIG> is configured as a lever arm.

Referring to <FIG>, the TR turning door <NUM> is movably coupled to the translating sleeve <NUM> and its sleeve segment <NUM>. The turning door pivot mounts <NUM> of <FIG>, for example, are pivotally connected to sleeve outer mounts (e.g., tabs) via pin connections, where each of the sleeve outer mounts is connected to the sleeve outer panel <NUM> within the sleeve channel <NUM>. The TR turning door <NUM> may thereby be pivotally connected (e.g., hinged) to the sleeve outer panel <NUM>.

Referring to <FIG>, the TR blocker door <NUM> includes a blocker door panel <NUM>, one or more blocker door pivot mounts <NUM> (one such mount visible in <FIG>) and one or more blocker door linkage mounts <NUM> and <NUM>. The blocker door panel <NUM> extends longitudinally (e.g., axially along the axial centerline <NUM> when the TR blocker door <NUM> is stowed; e.g., see <FIG>) between and to a first end <NUM> of the blocker door panel <NUM> and a second end <NUM> of the blocker door panel <NUM>. This blocker door first end <NUM> may be an axially forward end of the blocker door panel <NUM> when the TR blocker door <NUM> is in a stowed position (e.g., see <FIG>). The blocker door first end <NUM> may also be a radial inner end of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door stowed position (e.g., see <FIG>), and the blocker door first end <NUM> may be a radial outer end of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door deployed position (e.g., see <FIG>). By contrast, the blocker door second end <NUM> may be an axially aft end of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door stowed position (e.g., see <FIG>). The blocker door second end <NUM> may also be a radial outer end of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door stowed position (e.g., see <FIG>), and the blocker door second end <NUM> may be a radial inner end of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door deployed position (e.g., see <FIG>).

The blocker door panel <NUM> extends laterally (e.g., circumferentially or tangentially) between and to opposing sides <NUM> of the TR blocker door <NUM>. The blocker door panel <NUM> extends vertically (e.g., radially when the TR blocker door <NUM> is stowed; e.g., see <FIG>) between and to a front side <NUM> of the blocker door panel <NUM> and a back side <NUM> of the blocker door panel <NUM>. The blocker door front side <NUM> may be a radial inner side of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door stowed position (e.g., see <FIG>), and the blocker door front side <NUM> may be an axially forward side of the blocker door panel <NUM> when the TR blocker door <NUM> is in the turning door deployed position (e.g., see <FIG>). By contrast, the blocker door back side <NUM> may be a radial outer side of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door stowed position (e.g., see <FIG>), and the blocker door back side <NUM> may be an axially aft side of the blocker door panel <NUM> when the TR blocker door <NUM> is in the blocker door deployed position (e.g., see <FIG>).

Each of the blocker door pivot mounts <NUM> is connected (e.g., fixedly secured) to the blocker door panel <NUM> at its blocker door back side <NUM>. Each of the blocker door pivot mounts <NUM> projects out from the blocker door panel <NUM> and its blocker door back side <NUM> to a distal end of the respective blocker door pivot mount <NUM>. Each of the blocker door pivot mounts <NUM> of <FIG> is configured as a mounting tab.

Each blocker door linkage mount <NUM>, <NUM> is fixedly connected (e.g., fixedly secured) to the blocker door panel <NUM> at its blocker door back side <NUM>. Each blocker door linkage mount <NUM>, <NUM> projects out from the blocker door panel <NUM> and its blocker door back side <NUM>. The blocker door linkage mount <NUM> may be configured as a lost motion device. The blocker door linkage mount <NUM> of <FIG>, for example, is configured as a spring arm; e.g., L-shaped or a C-shaped leaf spring. The blocker door linkage mount <NUM> of <FIG> is configured as a lever arm and/or a mounting tab.

Referring to <FIG>, the TR blocker door <NUM> is movably coupled to the translating sleeve <NUM> and its sleeve segment <NUM>. The blocker door pivot mounts <NUM> of <FIG>, for example, are pivotally connected to at least one sleeve inner mount <NUM> (e.g., a frame) via pin connections, where the sleeve inner mount <NUM> is connected to the sleeve inner panel <NUM> within the sleeve channel <NUM>. The TR blocker door <NUM> may thereby be pivotally connected (e.g., hinged) to the sleeve inner panel <NUM>.

The turning door actuation linkage <NUM> of <FIG> is configured as a (e.g., fixed length) strut; e.g., a link, an arm, etc. The turning door actuation linkage <NUM> extends longitudinally between and to a first end of the turning door actuation linkage <NUM> and a second end of the turning door actuation linkage <NUM>. The turning door actuation linkage <NUM> is movably coupled to the turning door linkage mount <NUM> at the first end. The turning door actuation linkage <NUM> of <FIG>, for example, is pivotally connected to the turning door linkage mount <NUM> via a pin connection. The turning door actuation linkage <NUM> is also movably coupled to the blocker door linkage mount <NUM> at the second end. The turning door actuation linkage <NUM> of <FIG>, for example, is pivotally connected to the blocker door linkage mount <NUM> via a pin connection.

The blocker door actuation linkage <NUM> of <FIG> is configured as a (e.g., fixed length) strut; e.g., a link, an arm, etc. The blocker door actuation linkage <NUM> extends longitudinally between and to a first end of the blocker door actuation linkage <NUM> and a second end of the blocker door actuation linkage <NUM>. The blocker door actuation linkage <NUM> is movably coupled to the blocker door linkage mount <NUM> at the first end. The blocker door actuation linkage <NUM> of <FIG>, for example, is pivotally connected to the blocker door linkage mount <NUM> via a pin connection. The blocker door actuation linkage <NUM> is also movably coupled to a linkage mount at the second end, where the linkage mount is connected to an inner structure <NUM> of the nacelle <NUM> (also sometimes referred to as an inner fixed structure (IFS)). The blocker door actuation linkage <NUM> of <FIG>, for example, is pivotally connected to the nacelle inner structure <NUM> mount via a pin connection.

Briefly, the nacelle inner structure <NUM> is configured to house and provide an aerodynamic cover for a core of the gas turbine engine, which engine core typically include a compressor section, a combustor section and a turbine section of the gas turbine engine. The nacelle inner structure <NUM> of <FIG> and <FIG> is also configured to at least partially (or completely) form an inner peripheral boundary of the bypass flowpath <NUM>.

Referring to <FIG>, when the thrust reverser system <NUM> and each of its elements <NUM> and <NUM> are (e.g., fully, completely) stowed, each TR turning door <NUM> is arranged within an internal cavity <NUM> of the thrust reverser system <NUM>. A forward portion of this cavity <NUM> is formed by the structure channel <NUM>. An aft portion of the cavity <NUM> is formed by the sleeve channel <NUM>. Each TR turning door <NUM> may thereby be hidden (e.g., covered) from an exterior of the aircraft propulsion system <NUM> as well as the bypass flowpath <NUM> within the thrust reverser system <NUM> and its elements <NUM>, <NUM>, <NUM> and <NUM>. More particularly, a forward portion of the TR turning door <NUM> is located radially between, overlapped by and thereby covered by the structure outer wall <NUM> and the structure inner wall <NUM>. An aft portion of the TR turning door <NUM> is located radially between, overlapped by and thereby covered by the sleeve outer panel <NUM> and the sleeve inner panel <NUM>. The turning door actuation linkage <NUM> is also located and hidden within the cavity <NUM> and, more particularly, the sleeve channel <NUM>. The TR turning door <NUM> and the turning door actuation linkage <NUM> may thereby, for example, create no flow disturbance outside of the aircraft propulsion system <NUM> and/or within the bypass flowpath <NUM> when stowed.

Each stowed TR blocker door <NUM> may be received (e.g., nested) within a pocket in the translating sleeve <NUM> and its sleeve segment <NUM>. Each TR blocker door <NUM> of <FIG> is thereby flush with the sleeve inner panel <NUM>. With this arrangement, the TR blocker doors <NUM> and the sleeve inner panel <NUM> may form an aft portion of the outer peripheral boundary of the bypass flowpath <NUM>. Each TR blocker door <NUM> may thereby have a reduced impact on flow through the bypass flowpath <NUM> when stowed. The blocker door actuation linkage <NUM> may extend radially across the bypass flowpath <NUM> from the TR blocker door <NUM> to the nacelle inner structure <NUM>.

Referring to <FIG>, when the thrust reverser system <NUM> and each of its elements <NUM> and <NUM> are (e.g., fully, completely) deployed, each TR turning door <NUM> is moved (e.g., pivoted) to its deployed position. In this deployed position, each TR turning door <NUM> projects in a radial outward direction away from the translating sleeve <NUM> and its sleeve segment <NUM> and away from the axial centerline <NUM>. More particularly, each TR turning door <NUM> projects out from the sleeve channel <NUM>, through the thrust reverser flow passage <NUM> and out and away the rest of the nacelle <NUM> to its turning door first end <NUM>. Similarly, each TR blocker door <NUM> is moved (e.g., pivoted) to its deployed position. In this deployed position, each TR blocker door <NUM> projects in a radial inner direction away from the translating sleeve <NUM> and its sleeve segment <NUM> and towards the axial centerline <NUM>. More particularly, each TR blocker door <NUM> projects out of the thrust reverser flow passage <NUM> and into the bypass flowpath <NUM> to its blocker door second end <NUM>. With this arrangement, each TR blocker door <NUM> and the respective TR turning door <NUM> collectively form a turning vane. Each TR blocker door <NUM>, for example, may redirect bypass gas flowing aft within the bypass flowpath <NUM> radially outward into the thrust reverser flow passage <NUM>. The TR turning door <NUM> may turn the redirected bypass gas exiting the thrust reverser flow passage <NUM> in an axially forward direction. The thrust reverser system <NUM> may thereby be configured as a cascade-less thrust reverser system; e.g., a thrust reverser system configured without a thrust reverser cascade. This may eliminate costs and design complexities associated with including one or more thrust reverser cascades.

<FIG> illustrate a sequence of the thrust reverser system <NUM> and its element <NUM> and <NUM> being deployed. More particularly, <FIG> illustrate movement of the thrust reverser system elements <NUM> and <NUM> each moving from its stowed position to its deployed position. As illustrated by the movement from <FIG>, each TR turning door <NUM> and the respective TR blocker door <NUM> may (e.g., only) axially translate along the axial centerline <NUM> as the translating sleeve <NUM> moves from its stowed position of <FIG> to an intermediate position of <FIG>. However, as the translating sleeve <NUM> moves from the intermediate position of <FIG> to its deployed position of <FIG>, each TR turning door <NUM> and the respective TR blocker door <NUM> pivot to their deployed positions. This delayed pivoting of the TR turning door <NUM> and the TR blocker door <NUM> may be facilitated through the connection between the blocker door actuation linkage <NUM> and the TR blocker door <NUM>. For example, each mount <NUM> may flex as the translating sleeve <NUM> moves from the stowed position of <FIG> to the intermediate position of <FIG>. This flexure facilitates a slight movement between the blocker door actuation linkage <NUM> and the respective TR blocker door <NUM>. Since the first end of the blocker door actuation linkage <NUM> moves radially outward as the translating sleeve <NUM> moves from the stowed position of <FIG> to the intermediate position of <FIG>, the TR blocker door <NUM> is maintained in its horizontal position. However, as the translating sleeve <NUM> begins to move from the intermediate position of <FIG> to the deployed position of <FIG>, the blocker door actuation linkage <NUM> begins to pull on the respective TR blocker door <NUM> thereby pivoting that TR blocker door <NUM> radially inwards. The turning door actuation linkage <NUM> translates this movement of the respective TR blocker door <NUM> into movement (e.g., pivoting) of the respective TR turning door <NUM>.

Claim 1:
An assembly for an aircraft propulsion system (<NUM>), comprising:
an inner fixed structure; and
a thrust reverser system (<NUM>) comprising a cavity (<NUM>), a sleeve and a turning door (<NUM>);
the sleeve configured to translate along a centerline between a sleeve stowed position and a sleeve deployed position; and
the turning door (<NUM>) configured to move between a turning door (<NUM>) stowed position and a turning door (<NUM>) deployed position, the turning door (<NUM>) disposed within the cavity (<NUM>) when the sleeve is disposed in the sleeve stowed position, and the turning door (<NUM>) projecting in a radial outward direction away from the sleeve and the centerline when the sleeve is in the sleeve deployed position,
wherein the thrust reverser system (<NUM>) further comprises a blocker door (<NUM>) configured to move between a blocker door (<NUM>) stowed position and a blocker door (<NUM>) deployed position, wherein the blocker door (<NUM>) projects in a radially inward direction away from the sleeve and towards the centerline when the sleeve is in the sleeve deployed position, and wherein the blocker door (<NUM>) is pivotally connected to the sleeve,
characterised in that the thrust reverser system (<NUM>) further comprises a linkage pivotally connected to the blocker door (<NUM>) and the inner fixed structure, and the linkage extends radially across a bypass flowpath (<NUM>) when the blocker door (<NUM>) is in the blocker door (<NUM>) stowed position.