A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and
A system includes a turbomachine including a first chamber configured to contain a first fluid and a second chamber configured to contain a second fluid. The turbomachine also includes a barrier disposed between the first and second chambers. The barrier is configured to separate the first fluid and the second fluid. Additionally, the barrier includes a first surface facing the first chamber and a second surface facing the second chamber. The turbomachine also includes an orifice extending from the first chamber to the second chamber. The orifice defines a fluid passageway. Additionally, the turbomachine includes a tube including a first end and a second end. The first end is coupled to the first surface and is disposed about a perimeter of the orifice. The tube is configured to at least partially contain the second fluid.
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1. A system, comprising: a turbomachine, comprising: a combustion chamber;a first chamber configured to contain a first fluid;a second chamber configured to contain a second fluid;a barrier disposed between the first and second chambers, wherein the barrier is configured to separate the first fluid
1. A system, comprising: a turbomachine, comprising: a combustion chamber;a first chamber configured to contain a first fluid;a second chamber configured to contain a second fluid;a barrier disposed between the first and second chambers, wherein the barrier is configured to separate the first fluid and the second fluid, wherein the barrier comprises a first surface facing the first chamber and a second surface facing the second chamber;an orifice extending from the first chamber to the second chamber and defining a fluid passageway; anda tube comprising a first end and a second end, wherein the first end is coupled to the first surface and disposed about a perimeter of the orifice, wherein the tube is configured to at least partially contain the second fluid, and wherein the first chamber, the second chamber, and the tube are upstream of the combustion chamber of the turbomachine, wherein at least the first end of the tube is crosswise to the barrier, and the tube protrudes from the barrier in a direction against a purge flow through the tube. 2. The system of claim 1, wherein the tube comprises a first inner diameter at the first end and a second inner diameter at the second end, and wherein the second inner diameter is greater than the first inner diameter. 3. The system of claim 1, wherein an inner diameter of the tube progressively increases along a length of the tube from the first end to the second end. 4. The system of claim 1, wherein an inner diameter of the tube is constant along a length of the tube from the first end to the second end, and wherein a ratio of the inner diameter to the length is greater than approximately 2:1. 5. The system of claim 1, wherein the first chamber comprises a heat shield region disposed adjacent to the second chamber, wherein the second fluid comprise a fuel-air mixture, and wherein tube reduces a backflow of the fuel-air mixture into the heat shield region. 6. The system of claim 1, wherein the orifice comprises a liner cooling hole, an orifice along a hot gas path, a fuel injection port hole, or a fuel nozzle hole. 7. A method, comprising: separating a first fluid disposed in a first chamber and a second fluid disposed in a second chamber with a barrier of a turbomachine, wherein the barrier comprises a first surface facing the first fluid and a second surface facing the second fluid, the first fluid comprises a purge flow, and the second fluid comprises a hot gas or a fuel;enabling fluid passage from the first chamber to the second chamber through an orifice in the barrier and a tube extending from the first surface of the barrier; andcontaining the second fluid in the tube, wherein a backflow margin is increased by containing the second fluid in the tube;wherein the first chamber, the second chamber, and the tube are disposed upstream of a combustion chamber of the turbomachine. 8. The method of claim 7, comprising supplying the first fluid at a first pressure; and supplying the second fluid at a second pressure, wherein the first pressure is less than the second pressure. 9. The method of claim 8, comprising oscillating the first pressure or the second pressure due to operation of the turbomachine. 10. The method of claim 7, wherein the orifice comprises a liner cooling hole or an orifice along a hot gas path. 11. A system, comprising: a combustor comprising a combustion chamber;a first chamber disposed in the combustor and configured to flow a fuel;a second chamber disposed adjacent to the first chamber and configured to receive a purge flow;an orifice extending through a barrier disposed between the first chamber and the second chamber, wherein the orifice is configured to direct the purge flow from the second chamber to the first chamber; anda tube disposed about a perimeter of the orifice and coupled to the barrier, wherein the tube is configured to at least partially contain the fuel, and wherein the first chamber, the second chamber, and the tube are disposed upstream of the combustion chamber, and the tube extends radially from the barrier into the second chamber. 12. The system of claim 11, wherein the second chamber comprises a heat shield, and wherein the heat shield is disposed between the first chamber and an external wall of the combustor. 13. The system of claim 11, wherein the tube comprises a first end and a second end, wherein the first end is coupled to the barrier, and wherein a diameter of the tube increases along a length of the tube from the first end to the second end. 14. The system of claim 13, wherein the length of the tube is between approximately 2 and 6 centimeters. 15. The system of claim 11, wherein the tube is at least partially curved. 16. The system of claim 1, wherein the first chamber, the second chamber, and the tube are upstream of a fuel nozzle of the turbomachine. 17. The system of claim 1, wherein the first chamber, the second chamber, and the tube are separate from a fuel nozzle of the turbomachine. 18. The system of claim 1, wherein the purge flow is configured to flow through the orifice from the first chamber to the second chamber, and wherein the tube protrudes from the barrier into the first chamber. 19. The system of claim 1, wherein the first and second chambers are annular chambers, and wherein the first chamber is disposed about the second chamber. 20. The system of claim 11, wherein the first and second chambers are annular chambers, and wherein the second chamber is disposed about the first chamber.
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이 특허에 인용된 특허 (2)
Alkabie Hisham S,GBX, Combustor for gas- or liquid-fueled turbine.
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