Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/46
F01D-009/02
F01D-025/12
출원번호
US-0945948
(2010-11-15)
등록번호
US-9133721
(2015-09-15)
발명자
/ 주소
Lee, Ching-Pang
Morrison, Jay A.
출원인 / 주소
SIEMENS ENERGY, INC.
인용정보
피인용 횟수 :
0인용 특허 :
4
초록▼
A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion
A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
대표청구항▼
1. A transition duct for routing gas flow in a combustion turbine subsystem that includes 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, said circumferential direction having a tangential direc
1. A transition duct for routing gas flow in a combustion turbine subsystem that includes 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, said circumferential direction having a tangential direction component, an axis of the rotor assembly defining a longitudinal direction, and at least one combustor located longitudinally upstream of the first stage blade array and located radially outboard of the first stage blade array, said transition duct, comprising: a transition duct body having an internal passage extending between an inlet and an outlet:wherein the duct body is formed at least in part from a multi-panel outer wall; andwherein the multi-panel outer wall is formed from an upper section formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels, anda lower section formed from an inner panel having an inner surface that defines at least a portion of the hot gas path plenum, an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels and an outer panel positioned radially outward from the intermediate panel;an attachment system comprising at least one seal body integrally formed with the inner panel of the lower section and having at least one portion extending radially outward with at least one pocket configured to receive a side edge of the intermediate panel of the lower section in a sliding arrangement such that the intermediate panel is able to move in-plane relative to the attachment system and to receive a side edge of the outer panel in a sliding arrangement such that the outer panel is able to move in-plane relative to the attachment system. 2. The transition duct of claim 1, further comprising at least one rib extending from the inner panel of at least one of the upper and lower sections radially outward into contact with the intermediate panel. 3. The transition duct of claim 2, wherein the at least one rib comprises a plurality of ribs extending radially outward from at least one of the upper and lower sections. 4. The transition duct of claim 3, wherein the intermediate panel includes at least one depression between adjacent ribs such that a distance between the intermediate panel and the inner panel of at least one of the upper and lower sections is optimized. 5. The transition duct of claim 4, wherein the intermediate panel of at least one of the upper and lower sections is supported by the plurality of ribs, wherein a portion of the intermediate panel straddles a rib such that a support pocket is formed in the intermediate panel, wherein the support pocket is formed by a support side protrusion formed on each side of the rib, wherein each side of the support pocket extends radially inward toward the inner panel further than other portions of the intermediate panel. 6. The transition duct of claim 2, wherein the at least one rib is tapered such that a cross-sectional area of the at least one rib at the base is larger than a cross-sectional area of the at least one rib at an outer tip. 7. The transition duct of claim 1, wherein the inner panel of the upper section includes at least one film cooling hole and the intermediate panel of the upper section includes at least one impingement hole. 8. The transition duct of claim 1, wherein the inner panel of the lower section includes at least one film cooling hole, the intermediate panel of the lower section includes at least one impingement hole, and the outer panel of the lower section includes at least one metering hole. 9. The transition duct of claim 1, further comprising a sealing bracket releasably coupled to the at least one seal body such that the seal bracket imposes a compressive force directed radially inward on the inner and intermediate panels of the lower section. 10. The transition duct of claim 1, wherein the outer panel of the lower section is formed as a partial cylindrical structure such that at least two outer panels form a cylindrical structure, and wherein the intermediate panel of the lower section is formed as a partial cylindrical structure such that at least two intermediate panels form a cylindrical structure. 11. The transition duct of claim 1, further comprising an attachment system comprising at least one seal body integrally formed with the inner panel of the upper section and having at least one portion extending radially outward with at least one pocket configured to receive a side edge of the intermediate panel of the upper section in a sliding arrangement such that the intermediate panel is able to move in-plane relative to the attachment system. 12. The transition duct of claim 11, further comprising a sealing bracket releasably coupled to the at least one seal body such that the seal bracket imposes a compressive force directed radially inward on the inner and intermediate panels of the upper section. 13. The transition duct of claim 1, wherein the intermediate panel of the upper section is formed as a partial cylindrical structure such that at least two intermediate panels form a cylindrical structure.
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이 특허에 인용된 특허 (4)
Hsu, Johan; Morrison, Jay A., Cooling arrangement for a turbine component.
Zimmermann Achim (Mlheim a.d. Ruhr DEX) Beck Karl-Erhard (Berlin DEX) Mohr Klaus D. (Wuppertal DEX), Cylindrical combustion chamber housing of a gas turbine.
Morimoto, Hitoshi; Kanki, Hidenori; Ishiguro, Tatsuo; Shibata, Hiroki; Konishi, Tetsu; Sato, Kenji, Plates having cooling channels, and method for welding the plates and increasing a dimension of the cooling channels adjacent the welded section.
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