HYBRID COMBUSTOR ASSEMBLY AND METHOD OF OPERATION
First Claim
1. A hybrid combustion system for a propulsion system, the hybrid combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction, the hybrid combustion system comprising:
- a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall, wherein the nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer, the nozzle further defining a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle;
an inner liner extended generally along the longitudinal direction;
an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction;
a bulkhead wall disposed at the upstream end of the inner and outer liners, wherein the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and
a fuel manifold assembly extended at least partially through the bulkhead wall, wherein the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.
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Accused Products
Abstract
A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.
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Citations
20 Claims
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1. A hybrid combustion system for a propulsion system, the hybrid combustion system defining a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction, the hybrid combustion system comprising:
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a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall, wherein the nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, the nozzle inlet configured to receive a flow of oxidizer, the nozzle further defining a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle; an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, wherein the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, wherein the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11)
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12. A method of operating a combustion section for a propulsion system, the combustion section defining a rotating detonation combustion (RDC) system defining a RDC chamber, and wherein the combustion section further defines a fuel manifold assembly exits adjacent to a primary combustion chamber defined by an inner liner, and outer liner, and a bulkhead wall, the method comprising:
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providing a first flow of fuel through one or more of the plurality of fuel manifold assembly exits into the primary combustion chamber; providing a flow of oxidizer through the combustion section; igniting a mixture of the first flow of fuel and the oxidizer in the primary combustion chamber to generate a first flow of combustion gases; providing a second flow of fuel through a fuel injection port of the RDC system; mixing the second flow of fuel and the oxidizer in the RDC chamber; and igniting the mixture of the second flow of fuel and the oxidizer in the RDC chamber to generate a second flow of combustion gases. - View Dependent Claims (13, 14, 15, 16, 17, 18, 19, 20)
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Specification