Rotary pulse detonation system with aerodynamic detonation passages for use in a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-005/04
F02C-005/00
F02K-007/02
F02K-007/00
출원번호
US-0803293
(2004-03-18)
발명자
/ 주소
Venkataramani,Kattalaicheri Srinivasan
Butler,Lawrence
Lee,Ching Pang
출원인 / 주소
General Electric Company
인용정보
피인용 횟수 :
5인용 특허 :
4
초록▼
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferen
A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough. Each detonation passage further includes: a leading portion positioned adjacent the forward surface of the cylindrical member, with the leading portion having a centerline therethrough oriented at a designated angle to an axis extending substantially parallel to the longitudinal centerline axis within a specified plane; a trailing portion positioned adjacent the aft surface of the cylindrical member, with the trailing portion having a centerline therethrough oriented at a designated angle to the axis within the specified plane; and, a middle portion connecting the leading and trailing portions, with the middle portion having a centerline therethrough with a substantially constantly changing slope in the specified plane. A shaft is rotatably connected to the cylindrical member and a stator is configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator further includes at least one group of ports formed therein alignable with the leading portions of the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases interact therewith to create a torque which causes the cylindrical member to rotate.
대표청구항▼
What is claimed is: 1. A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at
What is claimed is: 1. A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one stage of circumferentially spaced detonation passages disposed therethrough, each said detonation passage further comprising: (1) 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; (2) 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, (3) 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; (b) a shaft rotatably connected to said cylindrical member; and, (c) a stator configured in spaced arrangement with said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portions of said detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases interact therewith to create a torque which causes said cylindrical member to rotate. 2. The pulse detonation system of claim 1, wherein said specified plane is oriented substantially parallel to a tangent of a circumference for said cylindrical member. 3. The pulse detonation system of claim 1, wherein said designated angle of said centerline for said leading portion is in a range of approximately 0째 to 75째 to said axis. 4. The pulse detonation system of claim 1, wherein said designated angle of said centerline for said trailing portion is in a range of approximately 0째 to-75째 to said axis. 5. The pulse detonation system of claim 1, wherein said designated angle of said leading portion and said designated angle of said trailing portion have a substantially equal magnitude. 6. The pulse detonation system of claim 1, wherein said designated angle of said leading portion and said designated angle of said trailing portion are oriented on opposite sides of said axis. 7. The pulse detonation system of claim 1, wherein said specified plane is oriented so as to be at a first angle to a first plane extending substantially parallel to a tangent of a circumference for said cylindrical member and at a second angle to a second plane extending substantially radially through said cylindrical member. 8. The pulse detonation system of claim 7, wherein said first angle is in a range of approximately 0째 to 75째. 9. The pulse detonation system of claim 7, wherein said second angle is in a range of approximately 0째 to 45째. 10. The pulse detonation system of claim 7, said designated angle of said centerline for said leading portion further comprising a first component in a range of approximately 0째 to 75째 with respect to said axis and a second component in a range of approximately 0째 to 45째 with respect to said axis. 11. The pulse detonation system of claim 7, said designated angle of said centerline for said trailing portion further comprising a first component in a range of approximately 0째 to-75째 with respect to said axis and a second component in a range of approximately 0째 to-45째 with respect to said axis. 12. The pulse detonation system of claim 1, wherein said port groups of said stator are oriented at a designated angle to said longitudinal centerline axis. 13. The pulse detonation system of claim 12, wherein designated angle of said port groups is greater than said designated angle of said leading portion for said detonation passages. 14. The pulse detonation system of claim 12, wherein said port groups are oriented at an angle to said longitudinal centerline axis in a range of approximately 45째 to 85째. 15. The pulse detonation system of claim 12, wherein a difference between said designated angle of said port groups and said designated angle of said leading portion is within a range of approximately 10째 to 65째. 16. The pulse detonation system of claim 1, further comprising at least one disk connecting said shaft and said rotatable cylindrical member. 17. The pulse detonation system of claim 1, wherein said detonation passages of each detonation stage are symmetrically spaced within said cylindrical member. 18. The pulse detonation system of claim 1, wherein said detonation passages are integral with said cylindrical member. 19. The pulse detonation system of claim 1, wherein said detonation passages are formed in replaceable segments connected to said cylindrical member. 20. The pulse detonation system of claim 1, further comprising a plurality of detonation stages in said cylindrical member. 21. The pulse detonation system of claim 20, said detonation passages of each said detonation stage being arranged in a substantially annular configuration through said cylindrical member having a distinct radius. 22. The pulse detonation system of claim 1, each said group of ports in said stator further comprising an air port in flow communication with a source of compressed air. 23. The pulse detonation system of claim 1, each said group of ports in said stator further comprising a fuel port in flow communication with a fuel source. 24. The pulse detonation system of claim 1, each said group of ports in said stator further comprising a port having a device for initiating a detonation wave associated therewith. 25. The pulse detonation system of claim 1, further comprising a plurality of port groups provided in said stator, wherein a plurality of detonation cycles occur in a predetermined timing and sequence in each said detonation passage during a revolution of said cylindrical member. 26. The pulse detonation system of claim 25, said stator including a predetermined amount of circumferential space between each said port group. 27. The pulse detonation system of claim 1, further comprising a seal plate positioned between said stator and said forward surface of said cylindrical member. 28. The pulse detonation system of claim 1, wherein a cross-sectional area through said detonation passages is substantially constant. 29. The pulse detonation system of claim 1, wherein a cross-sectional area through said leading and trailing portions of said detonation passages is not substantially constant. 30. A gas turbine engine having a longitudinal centerline axis extending 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 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 said drive shaft and interdigitated with said first compressor blade row; and, (c) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising: (1) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one detonation stage having a plurality of spaced detonation passages disposed therethrough and being connected to said drive shaft, each said detonation passage 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 engine 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; and, (2) a stator configured in spaced arrangement with said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portion of said detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases interface therewith to create a torque which causes said cylindrical member to rotate and power said fan section and said booster compressor. 31. A gas turbine engine having a longitudinal centerline axis extending therethrough, comprising: (a) a bellmouth at a forward end of said gas turbine engine; (b) a compressor positioned downstream of and in flow communication with said bellmouth, said compressor including a first compressor blade row and a second blade row connected to a drive shaft and interdigitated with said first compressor blade row; (c) a load connected to said drive shaft; and, (d) a pulse detonation system for powering said drive shaft, said pulse detonation system further comprising: (1) a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, said cylindrical member including at least one detonation stage having a plurality of detonation passages disposed therein and being connected to said drive shaft, each said detonation passage 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 engine 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; (2) a stator configured in spaced arrangement to said forward surface of said cylindrical member and a portion of said shaft, said stator including at least one group of ports formed therein alignable with said leading portion of said detonation passages as said cylindrical member rotates; wherein detonation cycles are performed in said detonation passages so that combustion gases interface therewith to create a torque which causes said cylindrical member to rotate and power said compressor and said load.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (4)
Louis G. Hunter, Jr. ; Kent W. Benner, Annular liquid fueled pulse detonation engine.
Janssen, Jonathan Sebastian; Tangirala, Venkat Eswarlu; Dean, Anthony John; Wiedenhoefer, James Fredric, Inlet airflow management system for a pulse detonation engine for supersonic applications.
Falempin, François; Le Naour, Bruno, Turbine engine including a continuous wave detonation chamber and cooling bypass flow and aircraft provided with such a turbine engine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.