Mounting for coupling a turbofan gas turbine engine to an aircraft structure
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/20
B64D-027/18
B64D-027/26
출원번호
US-0193857
(1994-02-09)
우선권정보
GB-0003468 (1993-02-20)
발명자
/ 주소
Udall Kenneth F. (Derbyshire GB2) Wright Eric (Nottinghamshire GB2) Drew David D. K. (Derby GB2)
출원인 / 주소
Rolls-Royce plc (London GB2 03)
인용정보
피인용 횟수 :
38인용 특허 :
0
초록▼
A turbofan gas turbine engine is provided with a polygonal rigid frame formed by a hub member, a plurality of radially extending spokes and a plurality of straight members connect to the radially outer ends of the spokes. The hub member is secured to the core casing and the straight members are secu
A turbofan gas turbine engine is provided with a polygonal rigid frame formed by a hub member, a plurality of radially extending spokes and a plurality of straight members connect to the radially outer ends of the spokes. The hub member is secured to the core casing and the straight members are secured to the core casing and the straight members are secured to the fan casing. Brackets are provided at two hard points at the radially outer ends of two adjacent hard points at the radially outer end of two adjacent spokes and brackets are provided at two hard points at the radially inner ends of two other spokes. The spokes have a chord length of six times that of conventional outlet guide vanes. The hard points are connected by links to a bracket at a first axial position on the aircraft stub pylon extension and the hard points are connect by links to a bracket at a second axial position on the stub pylon extension to form a rigid triangular structure to mount the engine from the aircraft.
대표청구항▼
A mounting for coupling a turbofan gas turbine to an aircraft structure for reacting side, axial, vertical, yaw, and thrust loads and pitch and roll couples, the turbofan gas turbine including an axis, a core engine and a fan, the core engine having a compressor, a combustor, a turbine and a core ca
A mounting for coupling a turbofan gas turbine to an aircraft structure for reacting side, axial, vertical, yaw, and thrust loads and pitch and roll couples, the turbofan gas turbine including an axis, a core engine and a fan, the core engine having a compressor, a combustor, a turbine and a core casing, the fan operating within a fan duct defined in part by a fan casing, the mounting comprising: a rigid frame defined by a hub member, a plurality of angularly spaced spokes secured at their radially inner ends to and extending radially outwardly from the hub member and an annular member secured to the radially outer ends of the spokes, the annular member secured to the fan casing and the hub member secured to the core casing, a first set of three attachment points on the aircraft structure, a second set of attachment points at an axial position on the aircraft structure different from the axial position of the first set of attachment points, the second set of attachment points having at least one attachment point, a first one of the attachment points in the first set of attachment points and the at least one attachment point in the second set of attachment points being arranged substantially in a plane containing the axis of the turbofan gas turbine engine and the first one of the attachment points of the first set of attachment points being positioned axially upstream of the at least one attachment point of the second set of attachment points, first connecting means connecting the radially outer ends of two adjacent spokes of the rigid frame with the first set of attachment points on the aircraft structure, the first connecting means comprising a first link connecting the first one of the attachment points of the first set of attachment points and the radially outer end of one of the two adjacent spokes, a second link connecting the first one of the attachment points of the first set of attachment points and the radially outer end of the other of the two adjacent spokes, a third link connecting a second one of the attachment points of the first set of attachment points and the radially outer end of the one spoke, a fourth link connecting a third one of the attachment points of the first set of attachment points and the radially outer end of the other of the two adjacent spokes, and a fifth link connecting the second one of the attachment points of the first set of attachment points and the radially outer end of the other of the two adjacent spokes, the first connecting means together with the rigid frame and the aircraft structure defining structure to react to the side, axial, vertical, and yaw loads and roll couplings, and second connecting means connecting the rigid frame with the second set of attachment points, the second connecting means comprising linkage means connected between the at least one attachment point of the second set of attachment points and a radially inner end of at least one spoke of the rigid frame, the second connecting means together with the rigid frame and the aircraft structure defining structure to react thrust loads and pitch couples.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허를 인용한 특허 (38)
Beier, Jürgen, Accessory mounting for a gas turbine engine.
Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E., Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor.
Diochon, Lionel; Mastroberti, Raffaella; Petrissans, Isabelle, Engine assembly for aircraft comprising an engine as well as a device for locking said engine.
Journade, Frédéric; Lafont, Laurent; Jalbert, Delphine, Engine assembly for an aircraft comprising attachments for engines offset below on the fan frame.
Suciu, Gabriel L.; Marx, Jon A.; Merry, Brian D.; Nordeen, Craig A.; Dye, Christopher M., Engine mounting configuration for a turbofan gas turbine engine.
Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
Suciu, Gabriel L.; Merry, Brian D.; Dye, Christopher M.; Johnson, Steven B.; Schwarz, Frederick M., Gas turbine engine with low stage count low pressure turbine.
Pautis, Olivier; Nanda, Rohan, Propulsion assembly incorporating a turbofan and a mounting pylon enabling a new distribution of the forces between the turbofan and the wing.
Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph B.; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph B.; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
Adams, Paul R.; Magge, Shankar S.; Staubach, Joseph Brent; Lord, Wesley K.; Schwarz, Frederick M.; Suciu, Gabriel L., Turbine section of high bypass turbofan.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.