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1. 发明公开

EP4242445A1 VARIABLE AREA NOZZLE ASSEMBLY 审中-公开
公开(公告)号：EP4242445A1
公开(公告)日：2023-09-13
申请号：EP23160603.9
申请日：2023-03-07
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/12 , F02K1/15
摘要： A variable area nozzle assembly (46) for a gas turbine engine includes a fixed structure (48) surrounding an exhaust duct (50) extending along a nozzle centerline (52). The fixed structure (48) includes an upper side and a lower side opposite the upper side (58). The variable area nozzle assembly (46) further includes a nozzle disposed about the nozzle centerline (52). The nozzle (54) includes a nozzle throat cross-sectional area and a nozzle outlet cross-sectional area downstream of the nozzle throat cross-sectional area. The nozzle includes an upper panel (74) and a lower panel (76). The upper panel (74) includes an upper downstream end (80) and the lower panel (76) including a lower downstream end (80). The upper downstream end (80) and the lower downstream end (80) define a portion of the nozzle throat cross-sectional area (86). The variable area nozzle assembly (46) further includes a nozzle actuation system (130) including an upper shaft (144) connected to the upper panel (76) and a lower shaft (162) connected to the lower panel (76).

2. 发明公开

EP4242444A1 THRUST REVERSER FOR VARIABLE AREA NOZZLE 审中-公开
公开(公告)号：EP4242444A1
公开(公告)日：2023-09-13
申请号：EP23160595.7
申请日：2023-03-07
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/12 , F02K1/00 , F02K1/62
摘要： A variable area nozzle assembly (46) for a gas turbine engine includes a fixed structure (48) surrounding an exhaust duct extending along a nozzle centerline. The fixed structure (48) further includes a first lateral side (62) and a second lateral side (64) opposite the first lateral side (62). The variable area nozzle assembly (46) further includes a nozzle (54). The nozzle (54) includes a nozzle outlet (119) including a nozzle outlet cross-sectional area. The variable area nozzle assembly (46) further includes a thrust reverser system (132) including a first thrust reverser door (134) and a second thrust reverser door (136). The first thrust reverser door (134) is pivotably mounted to the fixed structure (48) at the first lateral side (62). The second thrust reverser door (136) is pivotably mounted to the fixed structure (48) at the second lateral side (64). The first thrust reverser door (134) and the second thrust reverser door (136) define a portion of the nozzle outlet (119) of the nozzle.

3. 发明公开

EP4116567A1 HIDDEN DRAG LINK FOR THRUST REVERSER ASSEMBLY 审中-实审
公开(公告)号：EP4116567A1
公开(公告)日：2023-01-11
申请号：EP22183921.0
申请日：2022-07-08
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/74
摘要： A thrust reverser assembly (16) may comprise a cascade of vanes (114) and a sleeve (112) configured to translate relative to the cascade of vanes (114). The sleeve (112) may include an inner sleeve portion (120), an outer sleeve portion (122), and a pressure sleeve portion. The pressure sleeve portion may be located radially inward of the outer sleeve portion (122) and may extend forward from the inner sleeve portion (120). A blocker door may be hingedly coupled to the pressure sleeve portion. A drag link (154) may be pivotably coupled to the blocker door (150). A forward end of the drag link (154) may be configured to deploy radially inward in response to aft translation of the sleeve (112).

4. 发明公开

EP3892845A1 NACELLE WITH INDEPENDENT OPENING THRUST REVERSER SECTION 审中-实审
公开(公告)号：EP3892845A1
公开(公告)日：2021-10-13
申请号：EP21167264.7
申请日：2021-04-07
申请人： Rohr, Inc.
发明人： CHILUKURI, Radhakrishna , RAMLAOUI, Jihad , GORMLEY, Timothy
IPC分类号： F02K1/72 , B64D29/06 , B64D29/08
摘要： An assembly is provided for an aircraft propulsion system (20). This assembly includes a fixed structure (54) and a nacelle (22). The nacelle (22) includes a first fan cowl (36A) and a first thrust reverser section (100A) adjacent the first fan cowl (36A). The first fan cowl (36A) is movably attached to and arranged on a first side of the fixed structure (54). The first fan cowl (36A) is configured to move between a first fan cowl closed position and a first fan cowl second position. The first thrust reverser section (100A) is movably attached to and arranged on the first side of the fixed structure (54). The first thrust reverser section (100A) is configured to move between a first thrust reverser section closed position and a first thrust reverser section open position when the first fan cowl (36A) is in the first fan cowl closed position.

5. 发明公开

EP3763952A1 BARREL NUT RETAINER WITH ONE-WAY INSTALLATION GUIDE 审中-实审
公开(公告)号：EP3763952A1
公开(公告)日：2021-01-13
申请号：EP19212416.2
申请日：2019-11-29
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F16B37/04
摘要： An assembly is provided that includes a barrel nut (50), a barrel nut retainer (52) and a fastener (48). The barrel nut includes a threaded aperture (78). The barrel nut retainer includes a one-way installation guide (84). The fastener is configured to thread into the threaded aperture. The fastener is further configured to pass through the threaded aperture and project into the one-way installation guide when the fastener is inserted into the barrel nut retainer along a first direction.

6. 发明公开

EP3620641A1 THRUST REVERSER ACTUATION ARRANGEMENT DEPLOYABLE FAIRING SYSTEMS AND METHODS 有权
公开(公告)号：EP3620641A1
公开(公告)日：2020-03-11
申请号：EP19196031.9
申请日：2019-09-06
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy , GHANDOUR, Imad D.
IPC分类号： F02K1/11 , F02K1/70 , F02K1/76
摘要： A thrust reverser may include a frame (206), a track (220) disposed on the frame (206), a carrier (222) operatively coupled to the track (220), a first reverser door (202) operatively coupled to the carrier (222), the first reverser door (202) is movable relative to the frame (206), wherein the first reverser door (202) is configured to move to a first position in response to the carrier (222) moving with respect to the track (220) in a first direction, and move to a second position in response to the carrier (222) moving with respect to the track (220) in a second direction, and a deployable fairing (238) pivotally coupled to the frame (206), the deployable fairing (238) operatively coupled to the carrier (222), wherein the deployable fairing (238) is configured to move away from a central axis of the thrust reverser to provide clearance for the reverser door (202) to rotate into a deployed position.

7. 发明公开

EP3051112A1 TRANSLATING CASCADE HIDDEN BLOCKER DOOR THRUST REVERSER 有权
标题翻译： ÜBERSETZENDERKASKADENSCHUBUMKEHRER MIT VERSTECKTER BLOCKERKLAPPE
公开(公告)号：EP3051112A1
公开(公告)日：2016-08-03
申请号：EP16152997.9
申请日：2016-01-27
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/56 , F02K1/72 , F02K1/76
摘要： Aspects of the disclosure are directed to a thrust reverser system (200; 300; 400) of an aircraft comprising: a translating cascade sleeve (204; 304), a blocker door (328), and a kinematic mechanism configured to actuate the blocker door (328), the kinematic mechanism comprising: a first link (252) coupled to the translating cascade sleeve (204; 304), a second link (354) coupled to the first link (252) and a fixed structure (364), and a third link (356) coupled to the first link (252) and the blocker door (328).
摘要翻译：本发明的方面涉及一种飞行器的推力反向器系统（200; 300; 400），包括：平移级联套筒（204; 304），阻挡门（328）和运动机构，其构造成致动阻挡门（328），所述运动机构包括：耦合到所述平移级联套筒（204; 304）的第一连杆（252），联接到所述第一连杆（252）的第二连杆（354）和固定结构（364），以及联接到第一连杆（252）和阻挡器门（328）的第三连杆（356）。

8. 发明公开

EP4276299A2 DRIVE SYSTEM FOR TRANSLATING STRUCTURE 审中-实审
公开(公告)号：EP4276299A2
公开(公告)日：2023-11-15
申请号：EP23195529.5
申请日：2019-12-16
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： F02K1/76
摘要： A nacelle system having a translating structure is disclosed. In various embodiments, the system includes a fixed structure; a thrust reverser having a translating sleeve configured to translate relative to the fixed structure and in response to a first hydraulic system; and a variable area fan nozzle having a translating nozzle configured to translate relative to the translating sleeve and in response to a second hydraulic system. In various embodiments, the first hydraulic system and the second hydraulic system include a primary hydraulic actuator, the primary hydraulic actuator having a primary hydraulic fluid end and a primary gaseous fluid end; a secondary hydraulic actuator having a secondary hydraulic fluid end and a secondary gaseous fluid end; and a hydraulic supply line configured to fluidly couple the primary hydraulic fluid end of the primary hydraulic actuator to the secondary hydraulic fluid end of the secondary hydraulic actuator.

9. 发明公开

EP4209418A2 AIRCRAFT PROPULSION SYSTEM EXHAUST NOZZLE WITH EJECTOR PASSAGE(S) 审中-实审
公开(公告)号：EP4209418A2
公开(公告)日：2023-07-12
申请号：EP22214705.0
申请日：2022-12-19
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： B64D33/04 , F02K1/12 , F02K1/46 , F02K1/38 , F02K1/28
摘要： An apparatus is provided for an aircraft propulsion system (20). This apparatus includes an exhaust nozzle (40). The exhaust nozzle (40) includes a flowpath (52), a passage (58), an outer door (62), an inner door (63, 64) and an actuator (112) configured to move the outer door (62) and the inner door (63, 64) between an open arrangement and a closed arrangement. The flowpath (52) extends axially along a centerline (32) through the exhaust nozzle (40). The passage (58) extends laterally into the exhaust nozzle (40) to the flowpath when the outer door (62) and the inner door (63, 64) are in the open arrangement. The outer door (62) is configured to pivot inwards towards the centerline (32) when the outer door (62) moves from the closed arrangement to the open arrangement. The inner door (63, 64) is configured to pivot outwards away from the centerline (32) when the inner door (63, 64) moves from the closed arrangement to the open arrangement.

10. 发明公开

EP4108574A1 AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET 审中-实审
公开(公告)号：EP4108574A1
公开(公告)日：2022-12-28
申请号：EP22181379.3
申请日：2022-06-27
申请人： Rohr, Inc.
发明人： GORMLEY, Timothy
IPC分类号： B64D33/02 , F02C7/042
摘要： An assembly (58) for an aircraft propulsion system (20) includes a variable area inlet (66) with a fixed structure (70) and a moveable structure (72). The variable area inlet (66) is configured to open and close an airflow inlet passage (76) into the aircraft propulsion system (20). The moveable structure (72) is configured to move axially along a centerline (30, 78) between an aft position and a forward position. The moveable structure (72) includes an inlet lip structure (112) and a deflector (114). When the moveable structure (72) is in the aft position, the airflow inlet passage (76) is closed, and the deflector (114) is at least partially recessed into the fixed structure (70). When the moveable structure (72) is in the forward position, the airflow inlet passage (76) is opened axially between an aft end (126) of the inlet lip structure (112) and a forward end (116) of the fixed structure (70), and a forward end (134) of the deflector (114) is disposed axially at the forward end (116) of the fixed structure (70).

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