Combustor transition duct assembly with inner liner
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/00
F01D-025/26
F01D-009/02
출원번호
US-0541818
(2012-07-05)
등록번호
US-9476322
(2016-10-25)
발명자
/ 주소
Charron, Richard C.
Pierce, Daniel J.
출원인 / 주소
SIEMENS ENERGY, INC.
인용정보
피인용 횟수 :
0인용 특허 :
12
초록▼
A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct c
A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.
대표청구항▼
1. A transition duct assembly for a turbine engine comprising: a transition duct having a hollow body with an inner peripheral surface and an outer peripheral surface, the transition duct having an inlet and an outlet, the transition duct having an inlet end and an outlet end, the inner peripheral s
1. A transition duct assembly for a turbine engine comprising: a transition duct having a hollow body with an inner peripheral surface and an outer peripheral surface, the transition duct having an inlet and an outlet, the transition duct having an inlet end and an outlet end, the inner peripheral surface of the transition duct being convergent along a majority of the transition duct when moving from the inlet end to the outlet end thereof;an inner liner removably received within the transition duct, the inner liner having a generally hollow body with an inner peripheral surface and an outer peripheral surface, the outer peripheral surface of the inner liner being correspondingly convergent to the inner peripheral surface of the transition duct, and the inner peripheral surface defining an internal flow passage through the assembly;and wherein the inner liner is made of a plurality of separate segments including an upstream liner segment and a downstream liner segment, wherein the upstream liner segment is inserted from the inlet end of the transition duct and wherein the downstream liner segment is inserted from the outlet end of the transition duct. 2. The transition duct system of claim 1 wherein the transition duct is made of a different material than the inner liner. 3. The transition duct system of claim 1 wherein the inlet end of the transition duct includes a flange, wherein the inlet end of the inner liner includes a flange, wherein the flange of the transition duct engages the flange of the inner liner. 4. The transition duct system of claim 3 wherein the inlet end of the transition duct includes a recess to receive at least a portion of the flange of the inner liner, whereby the inlet end of the transition duct is substantially flush with the inlet end of the inner liner. 5. The transition duct system of claim 1 wherein the liner includes a plurality of holes therein generally extending from the inner peripheral surface to the outer peripheral surface. 6. The transition duct system of claim 1 wherein at least a portion of the inner peripheral surface of the inner liner is coated with a thermal insulating material. 7. The transition duct system of claim 1 wherein the transition duct has an associated longitudinal axis, wherein the longitudinal axis is substantially straight along the entire length of the transition duct, and wherein the inner liner is a single piece. 8. The transition duct system of claim 1 wherein the transition duct has an outlet end region and a longitudinal axis, wherein the transition duct is curved in the outlet end region of the liner such that the longitudinal axis of the liner is not substantially straight in the outlet end region. 9. The transition duct system of claim 1 wherein the upstream liner segment abuts the downstream liner segment. 10. The transition duct system of claim 1 wherein the upstream liner segment is attached to the downstream liner segment. 11. The transition duct system of claim 1 wherein the inner liner substantially matingly engages the inner peripheral surface of the transition duct. 12. The transition duct system of claim 1 wherein a plurality of protrusions extend from the inner peripheral surface of the transition duct, whereby the protrusions maintain the outer peripheral surface of the inner liner in spaced relation to the inner peripheral surface of the transition duct. 13. A combustion turbine subsystem, comprising: a first stage blade array having a plurality of blades extending in a radial direction from a rotor assembly for rotation in a circumferential direction about an axis of the rotor assembly;a plurality of combustors located upstream of the first stage blade array;a plurality of transition duct assemblies, each of the transition duct assemblies comprising:a transition duct having a hollow body with an inner peripheral surface and an outer peripheral surface, the transition duct having an inlet and an outlet, the transition duct having an inlet end and an outlet end, the inner peripheral surface of the transition duct being convergent along a majority of the transition duct when moving from the inlet end to the outlet end thereof;an inner liner removably received within the transition duct, the inner liner having a generally hollow body with an inner peripheral surface and an outer peripheral surface, the outer peripheral surface of the inner liner being correspondingly convergent to the inner peripheral surface of the transition duct, and the inner peripheral surface defining a flow passage through the assembly, the inner liner being made of a different material than the transition duct, each transition duct body being located between a respective combustor and the first stage blade array to receive the gas flow exhausted by the respective combustor into the internal passage through the inlet in the inner liner, the outlet of the inner liner discharging the gas flow from the internal passage directly to the first stage blade array, the internal passage of each duct being free of vanes, whereby the gas flow discharged from the outlet of each transition duct body flows to the first stage blade array without passing any flow turning vanes; andwherein the inner liner is made of a plurality of separate segments including an upstream liner segment and a downstream liner segment; wherein the upstream liner segment is inserted from the inlet end of the transition duct and wherein the downstream liner segment is inserted from the outlet end of the transition duct. 14. The combustion turbine subsystem of claim 13 wherein the inlet end of the transition duct includes a flange and a recess, wherein the inlet end of the inner liner includes a flange, wherein the flange of the inner liner being received in the recess such that inlet end of the transition duct is substantially flush with the inlet end of the inner liner. 15. The combustion turbine subsystem of claim 13 wherein each transition duct has an associated longitudinal axis, wherein the longitudinal axis is substantially straight along the entire length of the transition duct, and wherein the inner liner is a single piece. 16. The combustion turbine subsystem of claim 13 wherein the transition duct has an outlet end region and a longitudinal axis, wherein the longitudinal axis is substantially straight along a substantial portion of length of the transition duct, the transition duct is non-linear in the outlet end region of the liner such that the longitudinal axis of the liner is not substantially straight in the outlet end region. 17. The combustion turbine subsystem of claim 13 wherein, for at least one of the plurality of transition duct assemblies, the upstream liner segment abuts the downstream liner segment. 18. The combustion turbine subsystem of claim 13 wherein for at least one of the plurality of transition duct assemblies, the upstream liner segment is attached to the downstream liner segment.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (12)
Ryan,William R.; Bland,Robert J., Attachment system for ceramic combustor liner.
Bunker,Ronald Scott; Bailey,Jeremy Clyde; Widener,Stanley Kevin; Johnson,Thomas Edward; Intile,John C, Method and apparatus for cooling combustor liner and transition piece of a gas turbine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.