IPC분류정보
| 국가/구분 |
United States(US) Patent
등록
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| 국제특허분류(IPC7판) |
|
| 출원번호 |
US-0642787
(1975-12-22)
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발명자
/ 주소 |
- Vetter Earl E. (Mercer Island WA)
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| 출원인 / 주소 |
- The Boeing Company (Seattle WA 02) Aeritalia S.p.A. (Naples IT 03)
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| 인용정보 |
피인용 횟수 :
27 인용 특허 :
0 |
초록
▼
A pod for mounting a turbofan jet propulsion engine on a strut is constructed so that a common cowl and portions of the fan air duct and turbine exhaust duct can accomodate a plurality of different turbofan engines that have substantially the same thrust rating but have variations in structural dime
A pod for mounting a turbofan jet propulsion engine on a strut is constructed so that a common cowl and portions of the fan air duct and turbine exhaust duct can accomodate a plurality of different turbofan engines that have substantially the same thrust rating but have variations in structural dimensions. The portions of the pod common to all such engines include an annular cowl, an inlet throat that merges into the forward end of the cowl to form an inlet highlight, a rearward portion of the outer fan duct wall, a rearward portion of the inner fan duct wall and a turbine nozzle. The common portions of the pod structure are designed about a common datum plane orthogonally oriented relative to the pod center line. The rear face of the turbine casing of each of the turbofan jet propulsion engines is positioned in this datum plane when mounted in the pod. An annular inlet adapter forms an inlet wall that couples the rearward edge of the inlet throat to the forward, peripheral portion of the engine fan casing. Outer and inner fan duct wall adapters couple the common outer and inner portions of the fan duct walls to the engine fan casing at the datum plane. A fan nozzle adapter ring is attached to the rear portion of the cowl and the outer fan duct wall to provide an appropriately dimensioned fan nozzle exit opening. The turbine outlet of at least one of the engines can be coupled directly to the common nozzle of the pod. An annular adapter ring is coupled between the forward edge of the common nozzle and the rearward face of the turbine engine outlet on those engines having a lesser longitudinal dimension.
대표청구항
▼
A pod for housing a turbofan jet propulsion engine selected from a plurality of different turbofan engines, said engine having a fan casing, a fan, a turine engine a turbine engine casing and a turbine outlet, said fan casing having a forward end defining a fan entrance plane and a rearward end defi
A pod for housing a turbofan jet propulsion engine selected from a plurality of different turbofan engines, said engine having a fan casing, a fan, a turine engine a turbine engine casing and a turbine outlet, said fan casing having a forward end defining a fan entrance plane and a rearward end defining a fan exit plane, said pod comprising: an outer, annularly shaped, cowl member having a center line and a predetermined datum plane oriented transversely to the center line of said cowl member, said cowl member surrounding said center line and extending longitudinally from its forward end located forwardly of said datum plane to A rearward end located rearwardly of said datum plane, the forward end of said cowl member being radially convergent as it extends forwardly, an annular inlet throat adjacent the forward end of said cowl member and being disposed about said cowl center line, the forward end of said throat being radially divergent as it extends forwardly and merging with the forward enf of said cowl member to form an inlet highlight, said throat terminating in a rearward edge defining a throat oriented transversely to the cowl center line and located forwardly of datum said plane and forwardly from said fan entrance plane when said engine is positioned in said pod, an outer, angularly shaped, fan duct wall disposed about said cowl center line and being spaced radially inwardly from said cowl member, said outer fan duct wall having a forward end terminating in a forward edge defining a first plane oriented transversely to said center line, located rearwardly from said datum plane and spaced rearwardly from said fan exit plane when said engine is positioned in said pod, said outer fan wall having a rearward edge and being fixed to said cowl member adjacent the rearward end thereof, an annular turbine nozzle disposed about said cowl center line and spaced radially inwardly from said cowl member, the rearward end of said turbine nozzle forming a nozzle opening defining a turbine nozzle exit plane located rearwardly from said datum plane, said nozzle extending forwardly from said turbine nozzle exit plane and terminating in a forward edge defining a turbine nozzle entrance plane oriented transversely to said center line and positioned rearwardly from said datum plane, an inner, annularly spaced, fan duct wall spaced radially inwardly from said outer fan duct wall, the forward end of said inner fan duct wall terminating in a forward edge defining a second plane oriented transversely to said center line and located rearwardly from said datum plane, spaced rearwardly from said fan exit plane when said engine is positioned in said pool, and located forwardly of said turbine nozzle entrance, plane, said inner fan duct wall being located radially outwardly from said turbine engine casing when said engine is positioned in said pod, said inner fan duct wall converging toward said turbine nozzle as it extends rearwardly, and having a rearward end affixed to said turbine nozzle.
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