52 results about "Thrust reversal" patented technology

An aircraft nacelle provided with a thrust reversal device which comprises at least one diversion system which is configured to divert, in the activated state, an airflow channeled in the nacelle toward a lateral opening of the nacelle, at least one orientation system comprising at least one transverse deflector which is configured to orientate the airflow diverted by the diversion system in the radial directions and toward the upstream end of the nacelle, and at least one longitudinal deflector which is secant to the transverse deflector(s) and which is oriented in a direction which forms an angle of less than 25° with the longitudinal direction.

The invention relates to a thrust reverser (1) for an aircraft propulsion unit, the thrust reverser (1) comprising a stationary structure (3), a movable structure (13) that is translatable with respect to the stationary structure (3) between a thrust position and a thrust reversal position, at least one sealing membrane (17) designed to deflect at least part of the secondary flow towards the outside, at least one retention system (21) designed to engage with the stationary structure (3) and the corresponding sealing membrane (17), the retention system (21) being configured to subject the corresponding sealing membrane (17) to a return force comprising a component opposite to the general direction of flow in the thrust reversal position.

This invention discloses a drag reduction and thrust reversal device, relating to the field of fluid dynamics technology. The invention includes a front drag reduction air intake assembly, an automatic rotary cutting assembly, two fluid delivery pipes, and the drag reduction and thrust reversal assembly. The automatic rotary cutting assembly is mounted on the front drag reduction air intake assembly. In this invention, the drag reduction and thrust reversal device, composed of the front drag reduction air intake assembly, the automatic rotary cutting assembly, the fluid delivery pipes, and the drag reduction and thrust reversal assembly, efficiently captures oncoming fluid through an inclined inlet at the front. A filter baffle at the inlet blocks large debris, which is then shredded and mixed by fluid-driven rotary cutting blades. The mixture is then transported through the fluid pipes to the end delivery pipes. Under the action of the tail jet pressurization device, the fluid forms a vortex and is ejected at high speed, generating reverse thrust. This converts oncoming resistance into propulsive power, directly propelling the ship forward, achieving the dual effects of drag reduction and thrust reversal, and converting drag energy into forward propulsion.

The invention relates to an aircraft engine comprising a propulsion propeller rotating around a longitudinal axis (AX) and carrying blades (13), each blade (13) extending radially from a root (P) to a tip (S) along a span axis around which it is orientable, an air intake located downstream of the propeller and extending around the longitudinal axis (AX) to supply combustion members of the engine (1), the blades (13) being able to occupy a propulsion orientation to generate thrust oriented from upstream (AM) to downstream (AV) of the engine (1), and a thrust reversal orientation to generate thrust oriented from downstream (AV) to upstream (AM) of the engine. At the thrust reversal orientation, these blades (13) have at their roots (P) a pitch angle (Cp') relative to a plane (PS) normal to the longitudinal axis (AX) which is of opposite sign to their pitch angle (Cs') at their tips (S). Figure for abstract: Figure 5

An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state, at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system in radial directions and toward the upstream end of the nacelle, at least one longitudinal deflector configured to orient the air stream deflected by the deflection system in at least one direction that forms an angle with a radial direction.

The invention relates to a thrust reverser for an aircraft propulsion system, comprising a secondary flow sealing membrane (58) (21B) whose first end is connected to the fixed structure (31) of the reverser. This membrane bears against the upstream end (52a) of a radially internal wall (52) of a movable reverser cover and exerts on this upstream end (52a) a first force (70a) with a first axial component (72a) oriented downstream. Furthermore, the reverser is configured such that when the movable structure (29) is in its thrust reversal position, a membrane deployment element (62), such as a cable, exerts on a fastening or guiding element (64) integral with the movable cover, a second force (70b) with a second axial component (72b) oriented upstream. Figure for the abstract: Fig. 6

A propulsion assembly for an aircraft equipped with a thrust reverser comprising an actuator for moving a movable structure between an advanced direct thrust position and a retracted thrust reversal position, the propulsion assembly further comprising an actuator support device equipped with a first connecting part for connecting it to the deflection edge and / or to the outer shell of the intermediate casing, with a second connecting part for connecting it to a body of the actuator, and with a central part running axially between the shell and the actuator. Moreover, the actuator support device forms a guide for a set of cascades of the movable structure.

An air inlet of a nacelle of an aircraft propulsion assembly assembly comprising an inner wall and an outer wall which are connected upstream by an air inlet lip. The air inlet lip comprising thick portions and thin portions distributed alternately over the circumference of the air inlet lip. Each thick portion comprising an upstream leading edge to separate an upstream air flow into an outer air flow guided by the outer wall and an inner air flow guided by the inner wall during a thrust phase. Each thin portion comprising a downstream leading edge situated longitudinally downstream of each upstream leading edge so as to detach a reverse air flow at the air inlet lip during a thrust reversal phase.

The invention relates to an assembly (32) for a dual-flow aircraft turbomachine, comprising: - an inner shroud (42) configured to externally delimit a primary gas flow path (16) of the turbomachine; - an outer shroud (40) configured to internally delimit a secondary gas flow path (18) of the turbomachine; - at least one air discharge duct (46) extending between the inner shroud (42) and the outer shroud (40), the air discharge duct (46) opening into the secondary flow path (18) through an outlet orifice (52) equipped with discharge fins (54). According to the invention, at least some of the discharge fins (54) are mounted to be movable so as to be able to be controlled in incidence between a propulsion position and a thrust reversal position. Figure for the abstract: Figure 1.

An air intake (1) for an aircraft propulsion assembly (8) is disclosed, which extends along a longitudinal axis (X) and comprises a turbojet engine (7) comprising a primary flow path (4) and a secondary flow path (5) for guiding, respectively, a primary flow (F1) and a secondary flow during thrust, and a thrust reverser device for changing the secondary flow into a reversed flow (F-INV) during thrust reversal (B), the air intake (1) comprising a peripheral casing (11) comprising, in each plane radial to the axis (X), a point of maximum curvature (P) of the reversed flow (F-INV), a osculating circle of the radius of curvature defined at each point of maximum curvature (P), the average value (Rmoy) of the radii of curvature satisfying: Rmoy < 0.028*R3, with R3 being the internal radius of the air intake (1).

The present invention provides an omnidirectional anti-inclined surface missile based on thrust redirection, which includes a reverse wing assembly, an electric servo, an on-board control module, a warhead, a thrust reversal engine, a guidance component, a connecting cylinder, a flight engine, a tail wing assembly and a launch engine; the reverse wing assembly, the electric servo, the on-board control module, the warhead, the thrust reversal engine, the connecting cylinder, the flight engine, the tail wing assembly and the launch engine are sequentially connected from head to tail to form the missile; the guidance component is arranged at the tail of the thrust reversal engine and is located in the connecting cylinder at the same time; the electric servo executes actions according to control instructions to make the missile fly along the planned ballistic trajectory until it hits the target. The present invention can achieve omnidirectional strikes on buildings and has the ability to precisely strike and suppress targets in urban warfare.

A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

The invention relates to a thrust reverser (30) for an aircraft propulsion system through which a primary flow, a secondary flow, and a mixed flow (20C) pass. The reverser comprises a fixed structure (31) equipped with at least one flow deflection device (32), and a movable structure (29) comprising at least one reverser cover (33) radially delimiting outwards a mixed flow channel (21C) of the propulsion system, arranged downstream of the secondary flow channel (21B) and intended to be traversed by the mixed flow (20C). According to the invention, the reverser is designed such that when the movable structure (29) is in the thrust reversal position, a deployed sealing membrane (58) is arranged at least partially within the mixed flow channel (21C). Figure for the abstract: Fig. 3

The invention relates to a thrust reverser module (30) of a thrust reverser ring for an aircraft nacelle thrust reverser, characterized in that the thrust reverser module (30) comprises: - a first spar (32) which extends in a longitudinal direction (D) and carries blade elements (32a1, 32a2) each extending transversely relative to the longitudinal direction (D), the transverse blade elements (32a1, 32a2) being distributed along the first spar (32), - a second spar (34) which extends parallel and adjacent to the first spar (32), at least a portion of the transverse blade elements (32a1, 32a2) of the first spar (32) being connected to the second spar (34). Figure for abstract: Fig.2

The invention relates to a thrust reverser (30) for an aircraft propulsion system, the reverser comprising a movable structure (29) that can be moved in translation relative to a fixed structure (18) between an advanced position of direct thrust and a rearward position of thrust reversal, the reverser comprising an actuation system (70) for moving the movable structure, consisting of one or more actuators (70a, 70b1, 70b2) each comprising an actuation member (72) that is movable in translation and centered on an actuation axis (74), the two movable reverser hoods being arranged symmetrically with respect to each other along a first median plane (P1) of the reverser. According to the invention, among the actuator(s) of the actuation system (70), an eccentric actuator (70a) is provided, the actuation axis of which (74) is circumferentially offset with respect to the first median plane (P1). Figure for the abstract: Fig. 6

An air inlet of an aircraft propulsion unit comprising thrust reversal means configured to modify a bypass air flow circulating from upstream to downstream in a bypass duct into a reverse air flow circulating from downstream to upstream. The air inlet comprising an interior wall defining openings and, in each opening, a mobile member that comprises a covering wall and a deflecting wall and is mounted so as to pivot between a covering position, in which the covering wall obstructs the opening so as to guide the bypass air flow and promote a thrust phase, and a deflecting position, in which the deflecting wall obstructs the opening so as to separate the reverse air flow and promote a thrust reversal phase.

The invention relates to a thrust reverser for an aircraft propulsion system, the reverser comprising flow deflection means (32), as well as at least one deployable shut-off membrane (58) designed to direct at least a portion of the secondary flow circulating in the secondary stream towards the deflection means (32) when the reverser's moving structure is in the thrust reversal rearward position. The reverser also comprises a rear frame (60) for supporting the deflection means (32). According to the invention, the frame (60) is made in one piece, and one end (58a) of the deployable shut-off membrane (58) is engaged on a retaining rail (72) extending along the rear support frame (60), the retaining rail (72) being integrated into the rear support frame in one piece. Figure for the abstract: Fig. 9

A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.

An air intake for an aircraft propulsion assembly extending along a longitudinal axis and including a turbine engine that includes a primary flow path and a secondary flow path for respectively guiding a primary air flow and a secondary air flow during a thrust, and thrust reversal for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake including a peripheral external enclosure including, in each plane radial to the axis, a point of maximum curvature for detaching the reverse airflow, an osculating circle defining a radius of curvature that is defined at each of the points of maximum curvature. The average value of the radii of curvature being less than a product of 0.028 times an internal radius of the air intake at the fan.

Thrust reverser (100) comprising: a fixed structure (20) and a movable structure (21) mounted opposite an opening (22); an actuator (30-33) for selectively moving the movable structure (21) between a direct jet position and a thrust reversal position; wherein the thrust reverser (100) comprises a measuring device (91) for the distance between a first measuring point and a second measuring point which is integral with the movable structure (21), and one of the measuring points comprises a emitter (80) of a wave stream (82) and the other of the measuring points comprises a reflector element (83) for at least a portion of the wave stream (82). Figure for the abstract: Fig. 1

The invention relates to a thrust reverser for an aircraft propulsion assembly, comprising a fixed structure (31) and a movable structure (29), as well as a deployable deflection grid (32) which comprises a plurality of vane assemblies (32a) arranged successively in the axial direction. The thrust reverser also comprises a follower member (72) for connection between a rear grid support element (60) and the most downstream vane assembly (32a') of the grid, the member (72) being mounted movably relative to the assembly (32a') so as to adopt a retracted position when the movable structure (29) occupies its forward position for direct thrust, as well as a position of axial offset from the grid when the movable structure (29) occupies its rearward position for thrust reversal, in which the assembly (32a') is located axially further away from the rear grid support element (60) than in the forward position for direct thrust.

The invention relates to a thrust reverser for an aircraft propulsion assembly, the thrust reverser comprising a membrane (58) for closing the secondary duct, a second end of which membrane is connected to the inner wall of the secondary duct by a cable (62) that co-operates with an actuating device (70) for actuating this cable, wherein the device (70) comprises an elastic means (80) that co-operates with the second cable end (62b) of the deployment member (62), and wherein the reverser is configured such that, during an initial phase of the movement of the movable structure towards its retracted thrust reversal position, the elastic means (80) releases previously stored energy while urging the second cable end (62b), and such that, during a subsequent phase of this movement of the movable structure, the elastic means (80) stores energy while being urged by this second end (62b).

The invention relates to a gas turbine (10) for an aircraft. The gas turbine (10) comprises a housing (12) with an inner housing (14) (12) which has a main flow channel (16) for a main flow (H), and an outer housing (18) (12) which has a bypass channel (20) for a bypass flow (N), a water system (22) with a heat exchanger (24) which can be supplied with the main flow (H), and at least one exhaust channel (26) through which the main flow (H) can be directed from the main flow channel (16) through the heat exchanger (24) to at least one outlet nozzle (28) of the housing (12) to the outside.The housing (12) also has at least one thrust reverser flap (36) which is movable between a thrust reversal position in which the thrust reverser flap (36) can be acted upon by the main flow (H) and the bypass flow (N) to reverse the thrust of the gas turbine (10) and a flight position in which the thrust reverser flap (36) does not reverse the thrust of the gas turbine (10).

The system (101) herein comprises a local control module (120) and an analog wired connection, the local control module comprising an analog input port (121), the analog wired connection being located between the analog input (121) and a global control module (104), the analog wired connection referred to as a control connection (122). The local control module (120) is designed to receive a movement command from the global control module (104) through the control connection (122) and the analog input (121) to control the electric actuator (114) to move the cover (112). Furthermore, the local control module (120) comprises a transmission digital output (152) separate from the analog input (121), the local control module (120) being designed to transmit operational information from the thrust reversal system (101) through the digital output (120).

The invention relates to a thrust reverser for an aircraft propulsion unit, comprising a membrane (58) for closing the secondary flow path, a second end of which is connected to the internal wall of the secondary flow path by a cable (62) cooperating with an actuating device (70) for this cable, the device (70) comprising an elastic means (80) cooperating with the second cable end (62b) of the deployment member (62), and the reverser being configured so that during an initial phase of a movement of the mobile structure towards its retracted thrust reversal position, the elastic means (80) releases previously stored energy by stressing the second cable end (62b), and so that during a subsequent phase of this movement of the mobile structure, the elastic means (80) stores energy by being stressed by this second end (62b). Figure for abstract: Fig. 7

The invention relates to a thrust reverser for an aircraft propulsion system, the reverser comprising flow deflection means (32), as well as at least one deployable shut-off membrane (58) designed to direct at least a portion of the secondary flow circulating in the secondary stream towards the deflection means (32) when the reverser's moving structure is in the thrust reversal rearward position. The reverser also comprises a rear frame (60) for supporting the deflection means (32). According to the invention, the frame (60) is made in one piece, and one end (58a) of the deployable shut-off membrane (58) is engaged on a retaining rail (72) extending along the rear support frame (60), the retaining rail (72) being integrated into the rear support frame in one piece. Figure for the abstract: Fig. 9

The invention relates to a thrust reverser for an aircraft propulsion system, comprising a secondary flow sealing membrane (58), the second end of which is connected to the inner wall of the secondary flow by a cable (62) cooperating with an actuation device (70) for this cable, the device (70) comprising an elastic means (80) cooperating with the second end of the cable (62b) of the deployment member (62), and the reverser being configured such that during an initial phase of a movement of the movable structure towards its thrust reversal rearward position, the elastic means (80) releases previously stored energy by activating the second end of the cable (62b), and such that during a subsequent phase of this movement of the movable structure, the elastic means (80) stores energy by being activated by this second end (62b). Figure for the abstract: Fig. 7

An aircraft nacelle equipped with a thrust reversal device which comprises: at least one deflection system configured to deflect an air stream channeled in the nacelle toward a lateral opening of the nacelle, in the activated state; at least one orientation system having: at least one transverse deflector configured to orient the air stream deflected by the deflection system toward the upstream end of the nacelle, at least one downstream deflector positioned at the downstream edge of the lateral opening and configured to deflect the air stream deflected by the deflection system toward the upstream end of the nacelle.

The invention relates to a thrust reverser for an aircraft propulsion system, the reverser comprising a fixed structure (31) and a movable structure (29), as well as a deployable deflection grid (32) comprising several axially arranged fin assemblies (32a). It also includes a follower member (72) for connecting a rear grid support element (60) to the most downstream fin assembly (32a') of the grid, the member (72) being movable relative to the assembly (32a') so as to adopt a retracted position when the movable structure (29) is in its forward direct thrust position, and an axially offset position of the grid when the movable structure (29) is in its rearward thrust reversal position, in which the assembly (32a') is further axially away from the rear grid support element (60) than in the forward direct thrust position. Figure for the abridged version: Fig. 3