Pulse detonation system for a gas turbine engine having multiple spools
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-005/02
F02C-005/00
F02K-003/02
F02K-003/00
F02K-005/02
F02K-005/00
출원번호
US-0932169
(2004-09-01)
등록번호
US-7328570
(2008-02-12)
발명자
/ 주소
Venkataramani,Kattalaicheri Srinivasan
Butler,Lawrence
Davidson,James Paul
출원인 / 주소
General Electric Company
대리인 / 주소
Andes,William Scott
인용정보
피인용 횟수 :
5인용 특허 :
8
초록▼
A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compresso
A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation system.
대표청구항▼
What is claimed is: 1. A gas turbine engine having a longitudinal centerline axis therethrough, comprising: (a) a fan section at a forward end of said gas turbine engine including at least a first fan blade row connected to a first drive shaft; (b) a booster compressor positioned downstream of said
What is claimed is: 1. A gas turbine engine having a longitudinal centerline axis therethrough, comprising: (a) a fan section at a forward end of said gas turbine engine including at least a first fan blade row connected to a first drive shaft; (b) a booster compressor positioned downstream of said fan section, said booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with said first compressor blade row; and, (c) a pulse detonation system connected to and independently powering said first and second drive shafts. 2. The gas turbine engine of claim 1, wherein said pulse detonation system powers only said second drive shaft during a first designated condition of said gas turbine engine. 3. The gas turbine engine of claim 1, wherein said pulse detonation system powers both said first drive shaft and said second drive shaft during a second designated condition of said gas turbine engine. 4. The gas turbine engine of claim 3, wherein said first drive shaft is powered after said booster compressor rotates at a predetermined rotational speed. 5. The gas turbine engine of claim 3, wherein said second drive shaft is powered prior to said first drive shaft. 6. The gas turbine engine of claim 1, wherein a starting torque required to power said booster compressor is less than a starting torque required to power said fan section. 7. The gas turbine engine of claim 1, said pulse detonation system further comprising a first rotatable section for powering said second drive shaft. 8. The gas turbine engine of claim 7, said pulse detonation system further comprising a second rotatable section for powering said first drive shaft. 9. The gas turbine engine of claim 8, wherein said first rotatable section of said pulse detonation system is located upstream of said secondary section thereof. 10. The gas turbine engine of claim 8, wherein said first rotatable section of said pulse detonation system rotates independently of said second section thereof. 11. The gas turbine engine of claim 7, wherein said first rotatable section of said pulse detonation system includes a single stage for powering said second drive shaft. 12. The gas turbine engine of claim 8, wherein said second rotatable section of said pulse detonation system includes a plurality of stages for powering said first drive shaft. 13. The gas turbine engine of claim 12, wherein certain stages of said second rotatable section for said pulse detonation system have detonation cycles performed therein for a particular operating condition of said gas turbine engine. 14. The gas turbine engine of claim 1, further comprising a turbine positioned aft of and in flow communication with said pulse detonation system, wherein said turbine is also utilized to power said first drive shaft. 15. The gas turbine engine of claim 1, said pulse detonation system further comprising: (a) an air inlet duct in flow communication with said booster compressor, said air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough; (b) a fuel injector mounted to said air inlet duct in circumferentially spaced relation to each said port; (c) a device mounted to said air inlet duct in circumferentially spaced relation to each said fuel injector for initiating a detonation wave; (d) a first rotatable ring member positioned in coaxial relation around a first portion of said air inlet duct, said first ring member including at least one stage of detonation ducts disposed therein, wherein said first ring member is connected to said second drive shaft; and, (e) a second rotatable ring member positioned in coaxial relation around a second portion of said air inlet duct, said second ring member including at least one stage of detonation ducts disposed therein, wherein said second ring member is connected to said first drive shaft; wherein detonation waves are produced in said detonation stage of said first rotatable ring member during said first designated condition of said gas turbine engine so that combustion gases following each said detonation wave create a torque which causes said first ring member to rotate and power said second drive shaft. 16. The gas turbine engine of claim 15, wherein detonation waves are produced in at least certain stages of said second rotatable ring member during a second designated condition of said gas turbine engine so that combustion gases following each said detonation wave create a torque which causes said second ring member to rotate and power said first drive shaft. 17. The gas turbine engine of claim 1, said pulse detonation system further comprising: (a) a first rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said first rotatable cylindrical member including at least one stage of circumferentially spaced detonation passages disposed therethrough, wherein said first rotatable cylindrical member is connected to said second drive shaft; (b) a second rotatable cylindrical member located adjacent said first rotatable cylindrical member, said second rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface and including at least one stage of circumferentially spaced detonation passages disposed therethrough, wherein said second rotatable cylindrical member is connected to said first drive shaft; (c) a first stator configured-in spaced arrangement with said first rotatable cylindrical member, said first stator including at least one group of ports formed therein alignable with said detonation passages as said first cylindrical member rotates; and, (d) a second stator configured in spaced arrangement with said second rotatable cylindrical member, said second stator including at least one group of ports formed therein alignable with said detonation passages as said second cylindrical member rotates; wherein detonation cycles are performed in said detonation stage of said first rotatable cylindrical member during a first designated condition of said gas turbine engine to create a torque which causes said first rotatable cylindrical member to rotate and power said second drive shaft. 18. The gas turbine engine of claim 17, wherein detonation cycles are performed in at least certain detonation stages of said second rotatable cylindrical member during a second designated condition of said gas turbine engine to create a torque which causes said second rotatable cylindrical member to rotate and power said first drive shaft. 19. The gas turbine engine of claim 18, said detonation passages in said first and second rotatable cylindrical members further comprising: (a) a leading portion positioned adjacent said forward surface of said cylindrical member, said leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to said longitudinal centerline axis within a specified plane; (b) a trailing portion positioned adjacent said aft surface of said cylindrical member, said trailing portion having a centerline therethrough oriented at a designated angle to said axis within said specified plane; and, (c) a middle portion connecting said leading and trailing portions, said middle portion having a centerline therethrough with a substantially constantly changing slope in said specified plane. 20. The gas turbine engine of claim 17, said detonation passages of said first and second rotatable cylindrical members further comprising at least a portion thereof with a longitudinal axis extending therethrough which is oriented at a circumferential angle to said longitudinal centerline axis. 21. A method of independently powering separate drive shafts in a gas turbine engine by means of a pulse detonation system, comprising the following steps: (a) providing a first rotatable member with a plurality of detonation areas associated therewith; (b) connecting said first rotatable member to a first drive shaft of said gas turbine engine; (c) providing a second rotatable member with a plurality of detonation areas associated therewith; (d) connecting said second rotatable member to a second drive shaft of said gas turbine engine; (e) producing a torque on said first rotatable member via the performance of pulse detonation cycles in said detonation areas thereof during a first designated condition of said gas turbine engine; and, (f) producing a torque on said second rotatable member via the performance of pulse detonation cycles in said detonation areas thereof during a second designated condition of said gas turbine engine.
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이 특허에 인용된 특허 (8)
Louis G. Hunter, Jr. ; Kent W. Benner, Annular liquid fueled pulse detonation engine.
Venkataramani, Kattalaicheri Srinivasan; Butler, Lawrence; Lee, Ching Pang; Maclin, Harvey Michael, Integral pulse detonation system for a gas turbine engine.
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