Mixing-enhancement inserts for pulse detonation chambers
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-007/00
F02C-005/02
F02C-005/00
출원번호
UP-0127459
(2005-05-12)
등록번호
US-7520123
(2009-07-01)
발명자
/ 주소
Saddoughi, Seyed
Pinard, Pierre
Boespflug, Matthew
Steenburgh, Dennis
출원인 / 주소
Lockheed Martin Corporation
대리인 / 주소
Bracewell & Giuliani LLP
인용정보
피인용 횟수 :
3인용 특허 :
6
초록▼
The present invention provides a pulse detonation insert that induces flow obstructions within the pulse detonation chambers, wherein the flow obstructions are operable to induce turbulence within a primary fluid flow passing over the obstructions. This turbulence may take the form of vortices that
The present invention provides a pulse detonation insert that induces flow obstructions within the pulse detonation chambers, wherein the flow obstructions are operable to induce turbulence within a primary fluid flow passing over the obstructions. This turbulence may take the form of vortices that enhance the mixing of the oxidizer and fuel within the primary flow. Additionally, supports couple to the pulse detonation chamber walls and flow obstructions to hold the flow obstructions in place within the pulse detonation chamber. The combustion/Detonation of the mixed oxidizing fuel results in an increased velocity of the primary flow exiting the pulse detonation chamber and reduced the amount of unburnt fuel within the exhaust.
대표청구항▼
What is claimed is: 1. A pulse detonation engine comprising: an oxidizer source; a fuel source; a distribution manifold coupled to the oxidizer source and the fuel source, wherein the distribution manifold is operable to deliver mixed fuel and oxidizer; a pulse detonation chamber operable to receiv
What is claimed is: 1. A pulse detonation engine comprising: an oxidizer source; a fuel source; a distribution manifold coupled to the oxidizer source and the fuel source, wherein the distribution manifold is operable to deliver mixed fuel and oxidizer; a pulse detonation chamber operable to receive mixed fuel and oxidizer, wherein the pulse detonation chamber further comprises; an axis; containment walls operable to contain a pulse detonation; a thrust wall on which thrust is imparted by the pulse detonation, the thrust wall being axially upstream from the containment walls; an exhaust opening; an insert extending axially downstream from the thrust wall in a flow pathway of the mixed fuel and oxidizer within the pulse detonation chamber, the insert being free of contact with the containment walls, wherein the insert induces turbulence in the flow pathway of the mixed fuel and oxidizer and wherein the turbulence is operable to enhance mixing of the fuel and oxidizer; and an igniter positioned within the pulse detonation chamber operable to ignite the mixed fuel and oxidizer to produce the pulse detonation, wherein the insert further comprises: at least one flow obstruction operable to induce the turbulence within a primary flow comprising mixed fuel and oxidizer, the at least one flow obstruction comprising a ring that extends radially with respect to the axis, wherein the primary flow passes over the at least one flow obstruction and the turbulence is operable to enhance mixing of the oxidizer and fuel within the primary flow; and at least one support rod extending axially and coupled to the thrust wall, and operable to support the ring within the pulse detonation chamber. 2. The pulse detonation engine of claim 1, wherein the turbulence comprises vortices, and the at least one support rod comprises four support rods, each of which extends axially within the pulse detonation chamber. 3. The pulse detonation engine of claim 1, wherein the at least one flow obstruction comprises a plurality of discs. 4. The pulse detonation engine of claim 1, wherein combustion of the mixture of the oxidizer and fuel results in an increased velocity of the primary flow exiting the pulse detonation chamber, and the ring and the at least one support rod are coupled together with threads. 5. The pulse detonation engine of claim 1, wherein the at least one flow obstruction and at least one support are fabricated from materials resistant to a high pressure/temperature environment of the pulse detonation chamber, the igniter is located axially downstream from the thrust wall, and the insert extends axially downstream from the igniter. 6. The pulse detonation engine of claim 1, wherein the pulse detonation engine is a pulse detonation rocket or hybrid pulse detonation engine. 7. A pulse detonation actuator operable to be mounted at a fluid flow boundary wherein an exhaust of the pulse detonation actuator is operable to alter the fluid flow, wherein the pulse detonation actuator comprises: an oxidizer source; a fuel source; a distribution manifold coupled to the oxidizer source and the fuel source, wherein the distribution manifold is operable to deliver mixed fuel and oxidizer; a pulse detonation chamber operable to receive mixed fuel and oxidizer, wherein the pulse detonation chamber further comprises; an axis; containment walls operable to contain a pulse detonation; a thrust wall on which thrust is imparted by the pulse detonation, the thrust wall being axially upstream from the containment walls; an exhaust opening; an insert extending axially downstream from the thrust wall in a flow pathway of the mixed fuel and oxidizer within the pulse detonation chamber, the insert being free of contact with the containment walls, wherein the insert induces turbulence in the flow pathway of the mixed fuel and oxidizer and wherein the turbulence is operable to enhance mixing of the fuel and oxidizer; and an igniter positioned downstream from the thrust wall within the pulse detonation chamber operable to ignite the mixed fuel and oxidizer to produce the pulse detonation; the insert further comprises: at least one flow obstruction operable to induce the turbulence within a primary flow comprising mixed fuel and oxidizer, the at least one flow obstruction comprising, a series of rings that extend radially with respect to the axis, wherein the primary flow passes over the at least one flow obstruction and the turbulence is operable to enhance mixing of the oxidizer and fuel within the primary flow; and at least one support rod extending axially and coupled to the thrust wall, and operable to support the series of rings within the pulse detonation chamber. 8. The pulse detonation actuator of claim 7, wherein the turbulence comprises vortices, and the at least one support rod comprises four support rods, each of which extends axially within the pulse detonation chamber. 9. The pulse detonation actuator of claim 7, wherein combustion of the mixture of the oxidizer and fuel results in an increased velocity of the primary flow exiting the pulse detonation chamber, and the series of rings and the at least one support rod are coupled together with threads. 10. The pulse detonation actuator of claim 7, wherein the at least one flow obstruction and at least one support are fabricated from materials resistant to a high pressure/temperature environment of the pulse detonation chamber, and the insert extends axially downstream from the igniter.
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이 특허에 인용된 특허 (6)
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.
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