Slotted multi-nozzle grid with integrated cooling channels
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-009/30
F02K-009/97
출원번호
US-0647599
(2012-10-09)
등록번호
US-9115666
(2015-08-25)
발명자
/ 주소
Chasman, Daniel
Haight, Stephen D.
Villarreal, James K.
출원인 / 주소
Raytheon Company
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output. At least
An apparatus includes a slotted multi-nozzle grid with a plate having multiple elongated slotlettes through the plate. Each of at least some of the slotlettes has a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output. At least some of the slotlettes are arranged in multiple rows. The plate further includes multiple cooling channels through the plate. At least some of the cooling channels are located between the rows of slotlettes. Each cooling channel is configured to transport coolant through the plate in order to cool the plate, such as to cool the plate as hot combustion gases pass through the plate. Each of at least some of the rows may include at least two slotlettes, and two adjacent slotlettes in one row may be separated by a structural ligament (which may have a tear-drop cross-sectional shape).
대표청구항▼
1. An apparatus comprising: a slotted multi-nozzle grid comprising a plate configured to be connected to an outlet of a combustion chamber of a thruster and to allow combustion gases generated in the combustion chamber to flow in a longitudinal direction through the slotted multi-nozzle grid, the pl
1. An apparatus comprising: a slotted multi-nozzle grid comprising a plate configured to be connected to an outlet of a combustion chamber of a thruster and to allow combustion gases generated in the combustion chamber to flow in a longitudinal direction through the slotted multi-nozzle grid, the plate having a thickness in the longitudinal direction, the plate comprising: multiple slotlettes that extend through the thickness of the plate, each of the slotlettes elongated in a direction that is generally normal to the longitudinal direction, at least some of the slotlettes arranged in multiple rows and each of the multiple slotlettes having a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output; andmultiple cooling channels through the plate, at least some of the cooling channels located between the rows of slotlettes, each of the multiple cooling channels configured to transport coolant through the plate in order to cool the plate;wherein at least some of the rows include two or more of the at least some of the slotlettes. 2. The apparatus of claim 1, wherein two adjacent slotlettes in one row of the at least some of the rows are separated by a structural ligament. 3. The apparatus of claim 2, wherein the structural ligament has a tear-drop cross-sectional shape. 4. The apparatus of claim 1, wherein each convergent input and divergent output has substantially straight sides and rounded ends, each divergent output having a larger height than each convergent input. 5. The apparatus of claim 1, wherein: the at least some of the slotlettes in two adjacent rows have convergent inputs that angle towards one another and divergent outputs that angle towards one another; andone of the multiple cooling channels resides within an area between the convergent inputs and the divergent outputs of the at least some of the slotlettes in the two adjacent rows. 6. The apparatus of claim 1, wherein: the plate further comprises multiple ribs; andat least some of the ribs form a first portion of the at least some of the slotlettes in one row and a second portion of the at least some of the slotlettes in an adjacent row. 7. The apparatus of claim 6, wherein each of the at least some of the ribs has a tear-drop or airfoil cross-sectional shape. 8. The apparatus of claim 1, wherein each of the multiple cooling channels is substantially straight through the plate. 9. A system comprising: a thruster comprising a combustion chamber configured to generate combustion gases that flow in a longitudinal direction; anda slotted multi-nozzle grid connected to an outlet of the combustion chamber of the thruster and through which the combustion gases pass, the slotted multi-nozzle grid comprising a plate having a thickness in the longitudinal direction, the plate comprising: multiple slotlettes that extend through the thickness of the plate, each of the slotlettes elongated in a direction that is generally normal to the longitudinal direction, at least some of the slotlettes arranged in multiple rows and each of the multiple slotlettes having a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output; andmultiple cooling channels through the plate, at least some of the cooling channels located between the rows of slotlettes, each of the multiple cooling channels configured to transport coolant through the plate in order to cool the plate;wherein at least some of the rows include two or more of the at least some of the slotlettes. 10. The system of claim 9, wherein two adjacent slotlettes in one row of the at least some of the rows are separated by a structural ligament. 11. The system of claim 10, wherein the structural ligament has a tear-drop cross-sectional shape. 12. The system of claim 9, wherein each convergent input and divergent output has substantially straight sides and rounded ends, each divergent output having a larger height than each convergent input. 13. The system of claim 9, wherein: the plate further comprises multiple ribs; andat least some of the ribs form a first portion of the at least some of the slotlettes in one row and a second portion of the at least some of the slotlettes in an adjacent row. 14. The system of claim 13, wherein each of the at least some of the ribs has a tear-drop or airfoil cross-sectional shape. 15. The system of claim 9, wherein the thruster comprises a portion of a propulsion system on a vehicle. 16. A method of forming a slotted multi-nozzle grid, the method comprising: obtaining a plate having a thickness in a longitudinal direction;forming multiple slotlettes that extend through the thickness of the plate, each of the slotlettes elongated in a direction that is generally normal to the longitudinal direction, at least some of the slotlettes arranged in multiple rows and each of the multiple slotlettes having a convergent input, a divergent output, and a narrower throat portion separating the convergent input and the divergent output; andforming multiple cooling channels through the plate, each of the multiple cooling channels configured to transport coolant through the plate in order to cool the plate;wherein at least some of the cooling channels are located between the rows of slotlettes;wherein at least some of the rows include two or more of the at least some of the slotlettes; andwherein the plate is configured to be connected to an outlet of a combustion chamber of a thruster and to allow combustion gases generated in the combustion chamber to flow in the longitudinal direction through the slotted multi-nozzle grid. 17. The method of claim 16, wherein forming the slotted multi-nozzle grid comprises one of: machining the plate to form the multiple slotlettes and the multiple cooling channels; andmolding material to form the plate along with at least one of the multiple slotlettes and the multiple cooling channels. 18. The method of claim 16, wherein two adjacent slotlettes in one row of the at least some of the rows are separated by a structural ligament. 19. The method of claim 16, wherein: the plate further comprises multiple ribs; andat least some of the ribs form a first portion of the at least some of the slotlettes in one row and a second portion of the at least some of the slotlettes in an adjacent row. 20. The method of claim 16, wherein the thruster comprises a portion of a propulsion system on a vehicle.
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