Thrust reverser for an aircraft engine, pod assembly and corresponding powerplant
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/54
F02K-001/82
F02K-001/72
출원번호
US-0959384
(2015-12-04)
등록번호
US-9989010
(2018-06-05)
우선권정보
FR-14 61948 (2014-12-05)
발명자
/ 주소
Dussol, Loic
Dane, Jerome
Herisson, Hugo
출원인 / 주소
Airbus Operations (SAS)
대리인 / 주소
Greer, Burns & Crain, Ltd.
인용정보
피인용 횟수 :
0인용 특허 :
1
초록▼
A thrust reverser for an aircraft engine assembly, comprising two sub-assemblies configured to surround an engine, each of the sub-assemblies comprising an inner fixed structure, a translating cowl, a torque box, a substantially vertical 12 o'clock bifurcation, and a substantially vertical 6 o'clock
A thrust reverser for an aircraft engine assembly, comprising two sub-assemblies configured to surround an engine, each of the sub-assemblies comprising an inner fixed structure, a translating cowl, a torque box, a substantially vertical 12 o'clock bifurcation, and a substantially vertical 6 o'clock bifurcation. At least one of the sub-assemblies comprises at least one separating partition extending between the inner fixed structure, the translating cowl and the torque box of the sub-assembly, the separating partition being rigidly fixed to the inner fixed structure and the torque box, and connected to the translating cowl via a sliding connection.
대표청구항▼
1. A thrust reverser for an aircraft engine assembly, comprising: two sub-assemblies configured to surround an engine, each of said sub-assemblies comprising: an inner fixed structure,a translating cowl,a torque box,a substantially vertical 12 o'clock bifurcation, anda substantially vertical 6 o'clo
1. A thrust reverser for an aircraft engine assembly, comprising: two sub-assemblies configured to surround an engine, each of said sub-assemblies comprising: an inner fixed structure,a translating cowl,a torque box,a substantially vertical 12 o'clock bifurcation, anda substantially vertical 6 o'clock bifurcation,at least one of said sub-assemblies comprising:at least one separating partition rigidly fixed to said inner fixed structure of said sub-assembly and to said torque box of said sub-assembly, and connected to said translating cowl of said sub-assembly by a sliding connection; and,a blocker door connected at a first end to the inner fixed structure and at a second end, opposite the first end, to the translation cowl. 2. The thrust reverser according to claim 1, wherein at least a portion of a surface of the at least one separating partition comprises an air-porous outer layer and an inner layer defining chambers, said chambers being closed by said air-porous outer layer. 3. The thrust reverser according to claim 1, wherein said at least one separating partitions forms a one-piece assembly with at least a portion of said inner fixed structure. 4. The thrust reverser according to claim 1, wherein said at least one separating partition separates a first stream of airflow between said inner fixed structure, said substantially vertical 12 o'clock bifurcation, said translating cowl and said at least one separating partition, and a second airstream between said inner fixed structure, said substantially vertical 6 o'clock bifurcation, said translating cowl and said at least one separating partition. 5. The thrust reverser according to claim 1, wherein the thrust reverser defines a location configured to receive an engine extending along a longitudinal axis of a pod, and wherein, in each of said sub-assemblies: said inner fixed structure partially surrounds the location intended to receive said engine;said translating cowl at least partially surrounds said inner fixed structure, at a distance therefrom;said torque box at least partially surrounds said inner fixed structure, at a distance therefrom;said substantially vertical 12 o'clock bifurcation extends in a plane substantially parallel to the longitudinal axis of the pod and substantially vertical above the location configured for the engine, and rigidly connects said inner fixed structure and said torque box;said substantially vertical 6 o'clock bifurcation extends in a plane substantially parallel to the longitudinal axis of the pod and substantially vertical below the location configured for the engine, and rigidly connects said inner fixed structure and said torque box;said translating cowl being mobile in translation along an axis substantially parallel to the longitudinal axis of the pod, in relation to said inner fixed structure, to said torque box and to said substantially vertical 12 o'clock and substantially vertical 6 o'clock bifurcations, between: a first position wherein said torque box is in the extension of said translating cowl, such that said torque box and said translating cowl form a housing adapted to guide airflow flowing between said housing and said inner fixed structure in a direction substantially parallel to the longitudinal axis of the pod;a second position wherein an opening adapted to an airstream exists between said torque box and inner fixed structure. 6. The thrust reverser according to claim 5, wherein said at least one separating partition extends in a plane substantially parallel to the longitudinal axis of the pod, and is connected to said translating cowl by a sliding connection whose axis is substantially parallel to the longitudinal axis of the pod. 7. The thrust reverser according to claim 1, wherein said at least one separating partition extend in a plane forming an angle less than 40° with a horizontal plane. 8. The thrust reverser according to claim 7, wherein at least one of said sub-assemblies comprises a single separating partition which extends in a plane forming an angle less than 10° with the horizontal plane. 9. The thrust reverser according to claim 7, wherein at least one of said sub-assemblies comprises two separating partitions which extend in a plane forming an angle between 20° and 40° with the horizontal plane. 10. The thrust reverser according to claim 1, wherein said at least one separating partition extends over at least half the length of the thrust reverser. 11. The thrust reverser according to claim 10, wherein said at least one separating partition extends over at least 75% of the length of the thrust reverser. 12. The thrust reverser according to claim 1, wherein the blocker door is secured to the fixed inner structure with a rod. 13. The thrust reverser according to claim 12, wherein the blocker door is configured to move between two positions, an inactive position in which the blocker door is placed along the translating cowl, and an active position in which the blocker door is between the inner fixed structure and translating cowl. 14. A pod for an aircraft engine assembly, comprising a thrust reverser comprising: two sub-assemblies surrounding an engine, each of said sub-assemblies comprising: an inner fixed structure,a translating cowl,a torque box,a substantially vertical 12 o'clock bifurcation, anda substantially vertical 6 o'clock bifurcation,at least one of said sub-assemblies comprising:at least one separating partition rigidly fixed to said inner fixed structure of said sub-assembly and to said torque box of said sub-assembly, and connected to said translating cowl of said sub-assembly by a sliding connection; and,a blocker door connected at a first end to the inner fixed structure and at a second end, opposite the first end, to the translation cowl.
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이 특허에 인용된 특허 (1)
Sternberger, Joe E., Acoustic treated thrust reverser bullnose fairing assembly.
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