Pulse detonation engine having a scroll ejector attenuator
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-007/02
F23R-003/52
F23R-007/00
F02C-005/00
출원번호
US-0650523
(2012-10-12)
등록번호
US-9021783
(2015-05-05)
발명자
/ 주소
Hill, James D.
Cuozzo, Michael J.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Chisholm, Jr., Malcolm J.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30).
The engine (10) includes at least one firing tube (12) wherein an exhaust stream (32) from the firing tube (12) drives a turbine (30). A scroll ejector attenuator (40) is secured between and in fluid communication with an outlet end (28) of the firing tube (12) and an inlet (76) of the turbine (30). The attenuator (40) defines a turning, narrowing passageway (72) that extends a distance the exhaust stream (32) travels before entering the turbine (30) to attenuate shockwaves and mix the pulsed exhaust stream (32) into an even stream with minimal temperature differences to thereby enhance efficient operation of the turbine (30) without any significant pressure decline of exhaust stream (32) pressure and without any backpressure from the attenuator (40) on the firing tube (12).
대표청구항▼
1. A pulse detonation engine comprising: a. a plurality of firing tubes configured to direct an exhaust stream through outlet ends of the firing tubes;b. a turbine secured in fluid communication with the outlet ends of the plurality of firing tubes so that the exhaust stream passes into and drives t
1. A pulse detonation engine comprising: a. a plurality of firing tubes configured to direct an exhaust stream through outlet ends of the firing tubes;b. a turbine secured in fluid communication with the outlet ends of the plurality of firing tubes so that the exhaust stream passes into and drives the turbine; andc. a scroll ejector attenuator secured in fluid communication with and between the outlet ends of the plurality of firing tubes and the turbine, the scroll ejector attenuator including an ejector portion integral with a scroll attenuator portion wherein: i. the ejector portion includes an entry passage adjacent the outlet ends of the plurality of firing tubes for receiving and mixing the exhaust stream from the firing tubes and is configured to direct the exhaust stream to flow radially inward; andii. the scroll attenuator portion includes an exhaust stream flow tunnel that defines a circumferentially turning, narrowing passageway for directing flow of the exhaust stream from the entry passage of the ejector portion through the circumferentially turning, narrowing passageway and out of a discharge end of the scroll ejector attenuator adjacent an inlet of the turbine. 2. The pulse detonation engine of claim 1, wherein one of a cross-sectional area or a radius of an entry end of the circumferentially turning, narrowing passageway is greater than one of a corresponding cross-sectional area or a radius of the discharge end of the scroll ejector attenuator and cross-sectional areas or radii within the circumferentially turning, narrowing passageway decrease between the entry end and the discharge end of the scroll ejector attenuator. 3. The pulse detonation engine of claim 1, wherein a flow length of the circumferentially turning, narrowing passageway of the scroll attenuator portion is greater than an axial length of the scroll ejector attenuator, the axial length being a shortest distance between the entry passage and the discharge end of the scroll ejector attenuator, the flow length being an average distance the exhaust stream passes in transiting from the entry passage to the discharge end of the scroll ejector attenuator. 4. The pulse detonation engine of claim 1, wherein the ejector portion of the scroll ejector attenuator includes within the entry passage of the elector portion an impact wall for re-directing flow of the exhaust stream, wherein the impact wall is configured to be tangential to a flow direction axis parallel to flow of the exhaust stream passing out of the outlet end of the firing tube. 5. The pulse detonation engine of claim 1, further comprising at least a first firing tube and a second firing tube, and an ejector portion of the scroll ejector attenuator secured between the outlet ends of the first and second firing tubes and the circumferentially turning, narrowing passageway of the scroll attenuator portion, wherein the ejector portion defines an undivided entry passage configured to receive and mix exhaust streams from the at least first and second firing tubes. 6. The pulse detonation engine of claim 1, further comprising at least a first firing tube and a second firing tube, and an ejector portion of the scroll ejector attenuator secured between the outlet ends of the first and second firing tubes and the circumferentially turning, narrowing passageway, wherein the ejector portion defines a divided entry passage that defines at least a first entry manifold and second entry manifold configured so that the first entry manifold receives and mixes an exhaust stream from at least the first firing tube and the second entry manifold receives and mixes and exhaust stream from at least the second firing tube. 7. The pulse detonation engine of claim 6, wherein the scroll ejector attenuator defines a common passage in fluid communication with the first entry manifold and the second entry manifold, wherein the common passage is configured for receiving and mixing the exhaust streams from the first and second entry manifolds and for directing the mixed exhaust streams into the circumferentially turning, narrowing passageway. 8. The pulse detonation engine of claim 1, wherein the circumferentially turning, narrowing passageway of the scroll ejector attenuator results in the exhaust stream exiting the discharge end of the scroll ejector attenuator in a swirling orientation relative to a plane defined to be parallel to the discharge end of the scroll ejector attenuator. 9. A method of directing flow of an exhaust stream from a plurality of firing tubes into an inlet of a turbine of a pulse detonation engine, the method comprising: a. positioning a scroll ejector attenuator that has an ejector portion integrated with a scroll attenuator portion to form the scroll ejector attenuator so that an entry passage of the ejector portion is adjacent outlet ends of the plurality of firing tubes and so that a discharge end of the scroll attenuator portion of the scroll ejector attenuator is adjacent the inlet of the turbine; thenb. receiving and mixing the exhaust stream from the plurality of firing tubes outlet ends within an entry passage of the ejector portion of the scroll ejector attenuator and directing the exhaust steam radially inward; thenc. turning the flow of the mixed exhaust stream from a direction of the flow of the exhaust stream exiting the plurality of firing tubes to follow a flow path within a circumferentially turning, narrowing passageway defined within the scroll attenuator portion of the scroll ejector attenuator, wherein the flow path within the passageway is greater than an axial length between the entry passage and a discharge end of the scroll ejector attenuator; and thend. directing flow of the exhaust steam through the discharge end of the scroll attenuator portion of the scroll ejector attenuator and into the inlet of the turbine. 10. The method of directing flow of an exhaust stream of claim 9, further comprising directing a first exhaust stream from at least a first firing tube into a first entry manifold of a divided entry passage, directing a second exhaust stream from at least a second firing tube into a second entry manifold of the divided entry passage, mixing the exhaust stream from the first firing tube within the first entry manifold, mixing the exhaust stream from the second firing tube within the second entry manifold, directing flow of the first exhaust stream from the first entry manifold into a common passage, directing flow of the second exhaust stream from the second entry manifold into the common passage, mixing the first exhaust stream and the second exhaust stream within the common passage, and directing flow of the mixed first and second exhaust streams through the circumferentially turning, narrowing passageway of the scroll attenuator portion of the scroll ejector attenuator. 11. The method of directing flow of an exhaust steam of claim 9 further comprising directing flow of the exhaust stream through the charge end of the scroll attenuator portion of the scroll ejector attenuator so that the flow of the exhaust stream swirls relative to a plane defined to be parallel to the discharge end of the scroll ejector anttenuator.
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