A combustion chamber may include a first surface and a second surface interconnected by a wall forming a chamber having a central axis. The first surface may define an exhaust opening and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the c
A combustion chamber may include a first surface and a second surface interconnected by a wall forming a chamber having a central axis. The first surface may define an exhaust opening and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the central axis. A plurality of inlet ports may be configured to deliver air to the chamber. A plurality of fuel ports may be arranged on an inside of the second surface to deliver fuel to the chamber. The air flow from the inlet ports and fuel from the fuel ports may oppose each other to create a vortex of product proximal to the second surface.
대표청구항▼
1. A combustor comprising: a first surface and a second surface, parallel to the first surface, interconnected by a wall forming a chamber configured for combustion;the first surface defining a plurality of first openings, each first opening of the plurality of first openings comprising a frustoconi
1. A combustor comprising: a first surface and a second surface, parallel to the first surface, interconnected by a wall forming a chamber configured for combustion;the first surface defining a plurality of first openings, each first opening of the plurality of first openings comprising a frustoconical shape having an outer diameter and an inner diameter smaller than the outer diameter, and wherein at least one of air and fuel flow is configured to pass from the outer diameter through the inner diameter into the chamber; andthe second surface defining a plurality of second openings configured to receive fuel, wherein air flow from the plurality of first openings and fuel from the plurality of second openings are injected in substantially opposite directions to create a vortex of product proximal to the second surface;wherein the chamber has a central axis, the first surface defining an exhaust opening configured to exhaust product from the chamber and the second surface defining an inlet opening configured to supply at least one of fuel and air to the chamber, wherein the exhaust opening and the inlet opening align along the central axis of the chamber and wherein at least one of the plurality of first openings and the plurality of second openings are arranged about the central axis. 2. The combustor of claim 1, wherein the inner diameter of each first opening of the plurality of first openings is larger than a diameter of each second opening of the plurality of second openings. 3. The combustor of claim 1, wherein the plurality of first openings are offset from the wall. 4. The combustor of claim 3, wherein each of the plurality of first openings are equally offset from the wall. 5. The combustor of claim 1, wherein the inlet opening is configured to support the creation of the vortex of product. 6. The combustor of claim 5, further comprising a pilot at the inlet opening. 7. The combustor of claim 1, wherein a number of the plurality of first openings is greater than a number of the plurality of second openings. 8. The combustor of claim 1, wherein fuel flow from each of the plurality of second openings is configured to react with at least a portion of the product within the vortex. 9. A method of creating the vortex within the chamber of the combustor of claim 1, comprising: receiving air flow through the plurality of first openings and into the chamber at a first momentum, wherein the air flow is at an angle relative to the first surface; andreceiving fuel flow through the plurality of second openings and into the chamber at a second momentum, wherein the first momentum is greater than the second momentum to create the vortex of product proximal to the second surface. 10. The method of claim 9, further comprising: receiving a central flow including the at least one of fuel and air at a central injector positioned in the inlet opening of the second surface, wherein the central flow is injected in a substantially opposite direction from the air flow received through the plurality of first openings and into the chamber. 11. The method of claim 10, wherein a portion of the central flow leaves the chamber at the exhaust opening defined in the first surface. 12. The method of 11, wherein only the air flow is received through the plurality of first openings and wherein the air flow through the plurality of first openings is configured to collide with the central flow and direct a remaining portion of the central flow towards the second surface creating a recirculation flow. 13. A combustor, comprising: a first surface and a second surface interconnected by a wall forming a chamber configured for combustion;a plurality of inlet ports arranged in an interior of the chamber along the first surface, wherein each inlet port of the plurality of inlet ports includes an inlet port hole having an outer diameter and an inner diameter smaller than the outer diameter, and wherein at least one of air and fuel flow is configured to pass from the outer diameter through the inner diameter into the chamber; anda plurality of fuel ports arranged in the interior of the chamber along the second surface and configured to receive fuel, wherein each fuel port of the plurality of fuel ports includes a fuel port hole configured to deliver fuel into the chamber, wherein air from the inlet ports and fuel from the fuel ports are injected in substantially opposing directions to create a vortex of product proximal to the second surface;wherein the chamber has a central axis, the first surface defining an exhaust opening configured to exhaust product from the chamber and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the central axis of the chamber;wherein each inlet port of the plurality of inlet ports extends radially inwardly, with respect to the central axis, from outside of the chamber to the interior of the chamber towards the exhaust opening;wherein each fuel port of the plurality of fuel ports extends radially inwardly, with respect to the central axis, from an edge of the second surface outside of the chamber to the interior of the chamber to deliver fuel to the chamber. 14. The combustor of claim 13, wherein momentum of the air from the plurality of inlet port holes into the chamber is greater than momentum of the fuel from the plurality of fuel port holes into the chamber. 15. The combustor of claim 13, wherein each inlet port of the plurality of inlet ports defines the inlet port hole at an end of the inlet port to deliver air to the chamber. 16. The combustor of claim 15, wherein each inlet port hole of the plurality of inlet ports is angled at a same offset angle relative to the wall to form a continuous azimuthal air flow through the chamber. 17. The combustor of claim 13, wherein a number of the plurality of inlet ports is greater than a number of the plurality of fuel ports. 18. The combustor of claim 13, wherein the plurality of fuel ports are arranged such that fuel flow from a first fuel port is configured to react with combined air and fuel from an adjacent fuel port. 19. The combustor of claim 13, wherein the pilot opening is configured to deliver at least one of fuel and air into the chamber to create a central flow, wherein a portion of the central flow exits the chamber at the exhaust opening and a remaining portion of the central flow is abutted by the air from the plurality of inlet ports to create a recirculation flow surrounding the central flow.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (17)
Keller Jakob,CHX ; Fischer Jochem,DEX ; Muller Ulf Christian,CHX ; Reiss Frank,DEX ; Schiessel Pirmin,CHX, Burner arrangement for a gas turbine including an inlet-air impingement plate.
Knuth William H. ; Rice Eric E. ; Kohles Darin R. ; St. Clair Christopher P. ; Gramer Daniel J., Cryogenic solid hybrid rocket engine and method of propelling a rocket.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.