Main propulsion engine system integrated with secondary power unit
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-011/00
출원번호
US-0015439
(2001-12-13)
우선권정보
CA-2329555 (2000-12-22)
발명자
/ 주소
Albero, Jose
Dussault, Richard
Thompson, Robert G.
Germain, Patrick
Sahm, Michael K.
Tremaine, Eric
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Bachman &
인용정보
피인용 횟수 :
19인용 특허 :
7
초록▼
A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft
A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframer by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.
대표청구항▼
1. A power plant comprising:a nacelle cowl having an inlet end and an exhaust end; a primary gas turbine engine mounted within said nacelle cowl; said primary engine having a core compartment; secondary power means for providing pneumatic air to at least one load; said secondary power means being po
1. A power plant comprising:a nacelle cowl having an inlet end and an exhaust end; a primary gas turbine engine mounted within said nacelle cowl; said primary engine having a core compartment; secondary power means for providing pneumatic air to at least one load; said secondary power means being positioned within the core compartment; a by-pass passage positioned between said nacelle cowl and said core compartment; and said primary engine drawing air into said inlet end and a first portion of said air being diverted into said by-pass passage and a second portion of said air entering said primary engine. 2. A power plant according to claim 1, further comprising:an inner core cowl being concentrically mounted within said nacelle cowl about the primary gas turbine engine; and said by-pass passage comprising an annular by-pass passage extending between said nacelle cowl and said inner core cowl. 3. A power plant comprising:a nacelle cowl having an inlet end and an exhaust nozzle end; a primary gas turbine engine mounted within said nacelle cowl; said primary gas turbine engine having a core compartment; secondary power means for providing pneumatic air to at least one load; said secondary power means being positioned within the core compartment; an inner core cowl being concentrically mounted within said nacelle cowl about the primary gas turbine engine; an annular by-pass passage extending between said nacelle cowl and said inner core cowl; and said secondary power means having inlet means for drawing a fluid from said by-pass passage into said secondary power means. 4. A power plant according to claim 3, wherein said inlet is an axial inlet.5. A power plant according to claim 3, wherein said inlet means comprises a radial inlet plenum.6. A power plant according to claim 5, wherein said radial inlet plenum comprises a ring member defining a number of air passages extending radially through the core compartment.7. A power plant according to claim 3, further comprising said secondary power means having outlet means for directing expanded gases into said by-pass passage.8. A power plant according to claim 3, further comprising a closure member movable between a first position where fluid from said by-pass passage is drawn into said inlet means and a second position where fluid from said by-pass passage is prevented from being drawn into said inlet means.9. A power plant according to claim 1, wherein said primary gas turbine engine has a compressor section, a combustion section, and a turbine section.10. A power plant according to claim 1, wherein said secondary power means comprises an auxiliary power unit for providing pneumatic air to said at least one load.11. A power plant according to claim 10, wherein said auxiliary power unit comprises means for starting said primary gas turbine engine.12. A power plant according to claim 1, wherein said secondary power means comprises a gas turbine engine.13. A power plant according to claim 1, wherein said secondary power means comprises an auxiliary power unit having an environmental control system.14. A power plant according to claim 1, wherein said secondary power means comprises a power unit which integrates an auxiliary power unit, an energy power unit, an environmental control system, and an engine start system.15. A power plant according to claim 1, wherein said secondary power means comprises means for heating said primary gas turbine engine.16. A power plant according to claim 1, further comprising said secondary power means having an inlet for receiving air from said core compartment.17. A power plant according to claim 1, further comprising a hollow member for allowing ambient air to be drawn into said secondary power means.18. A power plant according to claim 1, further comprising a hollow member extending from an outlet end of said secondary power means for directing expanded gas to an ambient environment.19. A power plant according to claim 1, further comprising:an inner core cowl being concentrically mounted within and located radially inward of said nacelle cowl about the primary gas turbine engine; and said by-pass passage comprising an annular by-pass passage extending between said nacelle cowl and said inner core cowl. 20. A power plant for an aircraft, the power plant comprising:a nacelle having an inlet end, an exhaust end and a by-pass passage defined inside the nacelle; a gas turbine engine mounted in the nacelle for providing motive thrust to the aircraft; and a secondary power generation unit mounted inside the nacelle, said secondary power generation unit being adapted to provide at least one of pneumatic air and electrical power to an aircraft accessory system and having an inlet for drawing a fluid into said secondary power generation unit from the by-pass passage, wherein the gas turbine engine and said secondary power generation unit are mounted non-concentrically adjacent one another in the nacelle. 21. A power plant according to claim 20, wherein said inlet is an axial inlet.22. A power plant according to claim 20, wherein said inlet comprises a radial inlet plenum.23. A power plant according to claim 20, further comprising said secondary power generation unit has an outlet for directing expanded gases into the by-pass passage.24. A power plant according to claim 20, further comprising a closure member movable between a first position where fluid from said by-pass passage is drawn into said inlet and a second position where fluid from said by-pass passage is prevented from being drawn into said inlet.25. A power plant according to claim 20, wherein said secondary power generation unit comprises a gas turbine engine.26. A power plant according to claim 20, wherein said secondary power generation unit comprises an auxiliary power unit.27. A power plant for an aircraft, the power plant comprising:a nacelle having an inlet end, an exhaust end and an annular by-pass passage defined inside the nacelle; a thrust producing gas turbine engine core located radially inside the annular by-pass passage; and a secondary power unit located radially inside the annular by-pass passage and next to the engine core, said secondary power unit providing non-propulsive power to the aircraft. 28. A power plant according to claim 27, wherein said secondary power unit is located between said by-pass passage and said engine core.29. A power plant according to claim 27, wherein said secondary power unit has an inlet for drawing a fluid from said by-pass passage into said secondary power unit.30. A power plant according to claim 27, wherein said secondary power unit has an outlet for directing expanded gases into the by-pass passage.31. A power plant according to claim 27, wherein said secondary power unit comprises a gas turbine engine.32. A power plant according to claim 27, wherein said secondary power unit comprises an auxiliary power unit.
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이 특허에 인용된 특허 (7)
Ciokajlo John J. (Cincinnati OH) O\Brien Michael T. (Cincinnati OH), Air-start assembly and method.
Kisska, Michael K.; Princen, Norman H.; Kuehn, Mark S.; Cosentino, Gary B., Reverse flow engine core having a ducted fan with integrated secondary flow blades.
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