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1. 发明授权

US11554882B2 Attitude control and thrust boosting system and method for space launchers 有权
公开(公告)号：US11554882B2
公开(公告)日：2023-01-17
申请号：US16620249
申请日：2018-06-07
申请人： AVIO S.P.A.
发明人： Roberto Rosati
IPC分类号： B64G1/40 , F02K9/97 , F02K9/86 , B64G1/00 , F02K1/80
摘要： An attitude control and thrust boosting system (100) for a space launcher is disclosed, wherein the space launcher is equipped with a rocket engine (303) provided with an exhaust nozzle. The exhaust nozzle comprises a divergent portion (302) so designed as to make a supersonic gas flow exit through an exit section defined by a given angle of divergence with respect to a longitudinal axis of the rocket engine. The attitude control and thrust boosting system (100) comprises flaps (110, 111, 112, 113) that are arranged around the exit section, are shaped so as to extend the divergent portion of the exhaust nozzle, are mechanically decoupled from said exhaust nozzle and can be actuated to take different angular positions with respect to the longitudinal axis of the rocket engine. Control means (130) are also provided to receive quantities indicative of an actual attitude of the space launcher and an ambient static pressure, and to make the flaps (110,111,112,113) take a neutral angular position where the flaps (110,111,112,113) are inclined, with respect to the longitudinal axis of the rocket engine, according to an inclination angle greater than, or equal to, the given angle of divergence, in order to control the neutral angular position taken by the flaps (110,111,112,113) according to the ambient static pressure and to make one or more flaps (110,111,112,113) take an angular position different than the neutral angular position according to the actual attitude of the space launcher and to a required attitude for said space launcher.

2. 发明授权

US11535390B2 Structural panel with integrated coupler 有权
公开(公告)号：US11535390B2
公开(公告)日：2022-12-27
申请号：US17060964
申请日：2020-10-01
申请人： Rohr, Inc.
发明人： Kristopher B. Shaner , Thomas Sommer , Joseph R. Lundin
IPC分类号： B64D29/08 , B64D29/06 , F02K1/82 , F02K1/80 , B32B3/12
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a cowl door movable between a closed position and an open position. The cowl door includes a structural panel and a mount. The structural panel includes an inner skin, an outer skin and a cellular core. The cellular core is connected to and arranged between the inner skin and the outer skin. The mount includes a base and a coupler. The base is connected to and arranged between the inner skin and the outer skin. The coupler projects out from the base.

3. 发明申请

US20220341373A1 EJECTION CONE HAVING A FLEXIBLE AERODYNAMIC ATTACHMENT 有权
公开(公告)号：US20220341373A1
公开(公告)日：2022-10-27
申请号：US17640992
申请日：2020-09-02
申请人： SAFRAN CERAMICS
发明人： Eric CONETE , Benoit CARRERE
IPC分类号： F02K1/04 , F02K1/80 , F02K1/82
摘要： The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).

4. 发明授权

US11313320B2 Exhaust nozzle with centerbody support structure for a gas turbine engine 有权
公开(公告)号：US11313320B2
公开(公告)日：2022-04-26
申请号：US16803521
申请日：2020-02-27
申请人： Rolls-Royce North American Technologies Inc. , Rolls-Royce Corporation
发明人： David L. Sutterfield , Jack D. Petty , Bryan H. Lerg , Andrew Sanderson
IPC分类号： F02K1/04 , F02K1/80 , F02K1/08
摘要： An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

5. 发明授权

US11293378B2 Thrust reverser for an aircraft engine nacelle, comprising a panel for avoiding a movable slat of the wing, and nacelle associated therewith 有权
公开(公告)号：US11293378B2
公开(公告)日：2022-04-05
申请号：US16889154
申请日：2020-06-01
申请人： Safran Nacelles
发明人： Alexis Tabouret , Quentin Girardie , Jérôme Corfa , Matthieu Menielle , Fabrice Provost
IPC分类号： F02K1/72 , F02K1/80 , F02K1/76
摘要： A thrust reverser for a nacelle of an aircraft engine includes a movable cowl movable between a closed position in which thrust is not reversed and an open position for uncovering cascades reversing that reverse the direction of the cold air flow diverted from the annular secondary air flow path. The movable cowl includes a radially outer portion disposed proximate a leading edge of an aircraft wing and at least one avoidance panel on the radially outer portion designed to inhibit interference with a movable slat of the leading edge of the aircraft wing. The avoidance panel is pivotally mounted with respect to a fixed structure of the thrust reverser. At least one energy storing device constrains the avoidance panel to bear against the movable cowl, at least when the thrust reverser is in the closed position.

6. 发明授权

US11286814B1 Exhaust duct of gas turbine engine 有权
公开(公告)号：US11286814B1
公开(公告)日：2022-03-29
申请号：US17023945
申请日：2020-09-17
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Rabih Kassab
IPC分类号： F01D25/28 , F01D25/30 , F02K1/04 , F01D25/24 , F02K1/80 , F02C7/20 , F02K1/38
摘要： An exhaust duct of a gas turbine engine comprises a hub defining a radially-inner surface of a substantially annular exhaust gas path, and a strut extending into the exhaust gas path. The strut is attached to the hub via a first fastener at a forward fastening location closer to a leading edge of the strut than to a trailing edge of the strut, and via a second fastener at an aft fastening location closer to the trailing edge than to the leading edge. The second fastener is engaged with an appendage of the strut. The appendage is received into a receptacle formed in the hub open to the radially-inner surface.

7. 发明授权

US11280295B2 Beaded finger attachment 有权
公开(公告)号：US11280295B2
公开(公告)日：2022-03-22
申请号：US16299992
申请日：2019-03-12
申请人： ROHR, INC.
发明人： Richard Scott Alloway , Vijay V. Pujar , Stuart J. Byrne , Adam G. Saunders , Gary Euan Bowman
IPC分类号： F02K1/80 , F02C7/20 , F01D25/24 , F01D25/00 , F02K1/04 , F23R3/60
摘要： A nacelle system is disclosed. In various embodiments, the nacelle system may include a nacelle component; an attachment structure; and a bracket configured to secure the nacelle component to the attachment structure, the bracket comprising a first arm having a first bead structure disposed between a proximal end and a distal end of the bracket.

8. 发明申请

US20210404417A1 SEALING JOINT FOR AIRCRAFT TURBOJET ENGINE NACELLE 有权
公开(公告)号：US20210404417A1
公开(公告)日：2021-12-30
申请号：US17316118
申请日：2021-05-10
申请人： Safran Nacelles
发明人： Cédric RENAULT , Arnaud BONNY
IPC分类号： F02K1/80 , F02K1/72
摘要： A sealing joint for an aircraft turbojet engine nacelle includes a bead designed to be mounted in a joint support. The sealing joint is characterized in that the bead includes a retaining projection which extends in a direction substantially transverse to a longitudinal axis of the sealing joint, the retaining projection being designed to extend through the joint support when the sealing joint is mounted in the support thereof and/or a sealing lip which extends under the bead in a direction substantially parallel to the longitudinal axis of the sealing joint and which is designed to be compressed on the joint support when the sealing joint is mounted in the support thereof.

9. 发明授权

US11187186B2 Exhaust nozzle of a gas turbine engine 有权
公开(公告)号：US11187186B2
公开(公告)日：2021-11-30
申请号：US16719049
申请日：2019-12-18
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Predrag Todorovic , Thomas Schillinger
IPC分类号： F02K1/08 , F02K1/80 , F02K1/72 , F02K1/60 , F02K1/62 , F02K1/09
摘要： An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.

10. 发明授权

US11162416B2 Attritable engine integrated with vehicle 有权
公开(公告)号：US11162416B2
公开(公告)日：2021-11-02
申请号：US16222109
申请日：2018-12-17
申请人： United Technologies Corporation
发明人： Evan Butcher , Jesse R. Boyer , Om P. Sharma , Lawrence Binek , Bryan G. Dods , Vijay Narayan Jagdale
IPC分类号： F02C6/20 , F01D25/24 , B60K3/04 , B33Y10/00 , B33Y80/00 , F01D25/26 , F01D25/28 , F02C7/20 , F02K1/80
摘要： A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.

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