IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0096041
(2011-04-28)
|
등록번호 |
US-8276389
(2012-10-02)
|
발명자
/ 주소 |
- Charron, Richard C.
- Nordlund, Raymond S.
- Morrison, Jay A.
- Campbell, Ernie B.
- Pierce, Daniel J.
- Montgomery, Matthew D.
- Wilson, Jody W.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
18 인용 특허 :
4 |
초록
▼
An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented
An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.
대표청구항
▼
1. An arrangement for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement comprising: a plurality of interconnected integrated exit piece (IEP) sections defining an annular chamber oriented concentric to
1. An arrangement for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement comprising: a plurality of interconnected integrated exit piece (IEP) sections defining an annular chamber oriented concentric to a gas turbine engine longitudinal axis upstream of the turbine first stage blade section;each respective IEP comprising a first flow path section receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis there between, and delivering a partially bounded first flow to a downstream adjacent IEP section; andeach respective IEP further comprising a second flow path section receiving a partially bounded second flow from an upstream adjacent IEP and delivering at least part of the second flow to the turbine first stage blade section. 2. The arrangement of claim 1, wherein a first flow path section inner wall and a second flow path section inner wall share a common plane. 3. The arrangement of claim 1, wherein the first flow path section comprises a fully bounded throat region. 4. The arrangement of claim 1, wherein a first flow path section upstream end comprises a circular cross section, and wherein the first flow path section transitions to a non-circular cross section downstream of the first flow path section upstream end. 5. The arrangement of claim 4, wherein any flow path convergence conforms to the Witoszynski formula, and wherein for any converging area with a non-circular cross section an equivalent circular cross section is derived based on the non-circular cross section. 6. The arrangement of claim 5, wherein a downstream projection of a smallest circular cross section of the first flow path section entirely encompasses every non-circular cross section of the first flow path section, and wherein all dimensions of the non-circular cross sections of the first flow path section converge. 7. The arrangement of claim 1, wherein a first flow path section upstream end comprises a circular cross section. 8. An arrangement for delivering gasses from a plurality of combustors of a can annular gas turbine combustion engine to a turbine first stage blade section, the arrangement comprising a flow-directing structure for each combustor defining part of an overall gas flow path from the combustor to an annular chamber outlet, wherein each flow-directing structure comprises a cone and an integrated exit piece (IEP), wherein the cone receives a gas flow from a respective combustor and provides a cone-bounded flow path comprising a straight cone-bounded flow path longitudinal axis to the IEP; wherein the IEP comprises a first flow path coaxial with the cone-bounded flow path and configured to deliver the gas flow received from the cone to a downstream adjacent IEP second flow path, and a second flow path comprising an upstream end coaxial with an upstream adjacent IEP first flow path and configured to receive the gas flow from the upstream adjacent IEP first flow path and deliver at least a portion of the gas flow to the annular chamber outlet,wherein the first flow path and the second flow path are geometrically discrete,wherein each IEP comprises a first flow path wall and a second flow path wall that define respective abutting top and bottom sides of the first flow path and the second flow path respectively, wherein a first flow path wall flow-side surface and a second flow path wall flow-side surface share a common plane. 9. The arrangement of claim 8, wherein each IEP comprises a third flow path configured to receive a remaining gas flow from an upstream adjacent second flow path and deliver the remaining gas flow to the annular chamber outlet. 10. The arrangement of claim 8, wherein the cone-bounded flow path comprises a circular cross section, and the first flow path comprises a non-circular cross section. 11. The arrangement of claim 10, wherein in the first flow path with the non-circular cross section, flat walls are joined via fillets, and the fillets taper in a downstream direction. 12. The arrangement of claim 10, wherein the overall gas flow path comprises a bounded perimeter upstream portion and a partially unbounded perimeter downstream portion, wherein the first flow path comprises a throat region of non-zero throat length disposed in the bounded perimeter upstream portion and downstream of a region of transition from the circular cross section to the non-circular cross section of the bounded perimeter upstream portion. 13. The arrangement of claim 12, wherein the throat length is greater than or equal to ten percent of a hydraulic diameter of the throat region. 14. The arrangement of claim 12, wherein the throat acts as a nozzle from the bounded perimeter upstream portion to the partially unbounded perimeter downstream portion. 15. The arrangement of claim 14, wherein first flow path comprises part of the bounded perimeter upstream portion and part of the partially unbounded perimeter downstream portion. 16. The arrangement of claim 12, wherein any first flow path walls downstream of the throat region that partially bound the first flow path are effective to maintain a size, shape, and direction of a cross section of the first flow path as defined by the throat region. 17. The arrangement of claim 8, wherein the overall gas flow path comprises a bounded perimeter upstream portion and a partially unbounded perimeter downstream portion, wherein an upstream end of the partially unbounded perimeter downstream portion is disposed downstream of an upstream end of the first flow path and downstream of an upstream end of the second flow path. 18. The arrangement of claim 8, wherein the overall gas flow path comprises a bounded perimeter upstream portion and a partially unbounded perimeter downstream portion, wherein the bounded perimeter upstream portion comprises a transition from a circular cross section to a non-circular cross section, and wherein the transition is configured to produce a uniform velocity profile at a location where the transition is complete. 19. The arrangement of claim 18, wherein the transition comprises a uniform convergence profile. 20. The arrangement of claim 19, wherein the uniform convergence profile is based on the Witoszynski formula. 21. The arrangement of claim 20, wherein equivalent circular cross sections are derived for any non-circular cross sections, and the equivalent circular cross sections conform to the Witoszynski formula. 22. The arrangement of claim 21, wherein the equivalent circular cross sections comprise a diameter proportional to a largest dimension of the non-circular cross sections. 23. The arrangement of claim 21, wherein the equivalent circular cross sections comprise a diameter proportional to a hydraulic diameter of the non-circular cross sections. 24. The arrangement of claim 21, wherein a downstream projection of a smallest circular cross section of the overall gas flow path entirely encompasses every non-circular cross section of the overall gas flow path, and wherein all dimensions of the non-circular cross sections converge. 25. The arrangement of claim 10, wherein the cone-bounded flow path consists of circular cross sections. 26. An arrangement for delivering gasses from a plurality of combustors of a can annular gas turbine combustion engine to a turbine first stage blade section, the arrangement comprising a flow-directing structure for each combustor defining part of an overall gas flow path from the combustor to an annular chamber outlet, wherein each flow-directing structure comprises a cone and an associated integrated exit piece (IEP), wherein the cone receives a gas flow from a respective combustor and providing a cone-bounded flow path comprising a straight cone-bounded flow path longitudinal axis to the associated IEP; wherein IEPs together define an annular chamber oriented concentric to a gas turbine engine longitudinal axis and disposed upstream of the turbine first stage blade section;wherein the associated IEP and at least one downstream adjacent IEP comprise an IEP flow path that spans from a cone outlet to the annular chamber outlet, the IEP flow path comprising flow defining walls that receive the gas flow from the cone coaxial with the cone-bounded flow path and deliver the gas flow to the annular chamber;wherein flow-side surfaces of the flow defining walls that define boundaries of abutting areas of adjacent flows share a common plane; andwherein the flow defining walls initially entirely bound a perimeter of the IEP flow path, and wherein no flow defining walls separate adjacent flows at the annular chamber outlet. 27. The arrangement of claim 26, wherein at least a portion of each IEP flow path spans an additional downstream IEP. 28. The arrangement of claim 26, wherein the cone-bounded flow path comprises a circular cross section and the flow defining walls define a flow path comprising a non-circular cross section. 29. The arrangement of claim 28, wherein in the non-circular cross section, adjacent flow path walls are joined by a fillet and a radius of the fillet decreases in a downstream direction. 30. The arrangement of claim 26, wherein the overall gas flow path comprises a bounded perimeter upstream portion and a partially unbounded perimeter downstream portion, wherein the flow defining walls comprise a throat region of non-zero throat length disposed in the bounded perimeter upstream portion and downstream of all changes to a bounded perimeter upstream portion cross sectional shape. 31. The arrangement of claim 30, wherein the throat length is greater than or equal to ten percent of a hydraulic diameter of the throat region. 32. The arrangement of claim 30, wherein the throat acts as a nozzle from the bounded perimeter upstream portion to the partially unbounded perimeter downstream portion. 33. The arrangement of claim 30, wherein interior surfaces of flow defining walls downstream of the throat region match an interior boundary of downstream projections of throat region walls. 34. The arrangement of claim 26, wherein the overall gas flow path comprises a bounded perimeter upstream portion and a partially unbounded perimeter downstream portion, wherein the bounded perimeter upstream portion comprises a transition from a circular cross section to a non-circular cross section, and wherein the transition is configured to produce a uniform velocity profile at a location where the transition is complete. 35. The arrangement of claim 26, wherein any overall gas flow path convergence conforms to the Witoszynski formula, and wherein for any converging area with a non-circular cross section an equivalent circular cross section is derived based on the non-circular cross section. 36. The arrangement of claim 26, wherein a downstream projection of a smallest circular cross section of the overall gas flow path entirely encompasses every non-circular cross section of the overall gas flow path, and wherein all dimensions of the non-circular cross sections converge. 37. The arrangement of claim 26, wherein the cone-bounded flow path consists of circular cross sections. 38. An arrangement for delivering gasses from a plurality of combustors of a can annular gas turbine combustion engine to a turbine first stage blade section, the arrangement comprising a flow-directing structure for each combustor defining part of an overall flow path from the respective combustor to an annular chamber outlet, wherein each flow-directing structure comprises a cone and an integrated exit piece (IEP), wherein the cone receives a gas flow from a respective combustor and delivers the gas flow to the IEP; wherein the cone defines a fully bounded, circular cross section, axially straight, converging first portion of the overall flow path,wherein the IEP defines a fully bounded, circular cross section to non-circular cross section, second portion of the overall flow path coaxial with the first portion, wherein the overall flow path at a downstream end of the second portion comprises a collimated flow, andwherein the IEP and at least one downstream adjacent IEP define a partially bounded, third portion of the overall flow path, wherein an upstream end of the third portion partially bounds a flow path cross section that is coaxial with the second portion and has a same cross section shape as a second portion downstream end cross section shape, and wherein the third portion delivers the gas flow to the annular chamber outlet. 39. The arrangement of claims 38, wherein the third portion of the overall flow path requires an additional downstream IEP. 40. The arrangement of claims 38, wherein surfaces that define boundaries of abutting areas of adjacent flows share a common plane. 41. The arrangement of claims 38, wherein the second portion of the overall flow and the third portion of the overall flow path share common flow defining walls in the IEP. 42. The arrangement of claim 38, wherein the second portion of the overall flow path comprises a fully bounded throat region. 43. The arrangement of claim 38, wherein any overall flow path convergence conforms to the Witoszynski formula, and wherein for any converging area with a non-circular cross section an equivalent circular cross section is derived based on the non-circular cross section. 44. The arrangement of claim 43, wherein a downstream projection of a smallest circular cross section in the second portion entirely encompasses every non-circular cross section in the second portion, and wherein all dimensions of the non-circular cross sections converge. 45. The arrangement of claim 38, wherein a first flow path section upstream end comprises a circular cross section. 46. The arrangement of claim 38, wherein the non-circular cross section comprises a fillet and wherein the fillet decreases in radius in a downstream direction. 47. An arrangement for delivering gasses from a plurality of combustors of a can annular gas turbine combustion engine to a turbine first stage blade section, the arrangement comprising a flow-directing structure for each combustor defining part of an overall flow path from the respective combustor to an annular chamber outlet, wherein each flow-directing structure comprises a cone and an IEP, wherein the cone receives a gas flow from a respective combustor and delivers the gas flow to the integrated exit piece (IEP); wherein the cone defines a fully bounded, circular, straight, converging first portion of the overall flow path,wherein the IEP defines a fully bounded, circular cross section to non-circular cross section, second portion of the overall flow path coaxial with the first portion, wherein the overall flow path at a downstream end of the second portion comprises a collimated flow, andwherein the IEP and at least one downstream adjacent IEP define a partially bounded, third portion of the overall flow path, wherein an upstream end of the third portion partially bounds a flow path cross section that is initially coaxial with and matches a second portion downstream end cross section shape, and wherein the third portion delivers the gas flow to the annular chamber outlet,wherein surfaces of the IEP that define boundaries of abutting areas of adjacent flows share a common plane, wherein the second portion of the overall flow and the third portion of the overall flow path share common flow defining walls, and wherein the second portion of the overall flow path comprises a fully bounded throat region,wherein the overall flow path conforms to the Witoszynski formula, and wherein for any converging area with a non-circular cross section an equivalent circular cross section is derived based on the non-circular cross section,wherein a downstream projection of a smallest circular cross section in the second portion entirely encompasses every non-circular cross section in the second portion, and wherein all dimensions of the non-circular cross sections converge, andwherein a first flow path section upstream end comprises a circular cross section.
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