[특허]Ducting arrangement for cooling a gas turbine structure

SIEMENS ENERGY, INC.

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Ducting arrangement for cooling a gas turbine structure

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-009/06 F23R-003/02 F23R-003/06 F23R-003/54 F01D-009/02 F23R-003/00
출원번호	US-0655675 (2012-10-19)
등록번호	US-9085981 (2015-07-21)
발명자 / 주소	Lee, Ching-Pang Morrison, Jay A.
출원인 / 주소	SIEMENS ENERGY, INC.
인용정보	피인용 횟수 : 1 인용 특허 : 21

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A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of t...

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1. A ducting arrangement for a can annular gas turbine engine, comprising: a duct disposed between a combustor and a first row of turbine blades and defining a hot gas path therein, the duct comprising raised geometric features incorporated into a duct outer surface;a flow sleeve defining a cooling flow path between an inner surface of the flow sleeve and the duct outer surface; anda plurality of refresher cooling holes through the flow sleeve establishing fluid communication between a plenum surrounding the ducting arrangement and the cooling flow path;wherein the flow sleeve is configured to direct a flow of cooling fluid in the cooling flow path in a direction against a direction of a flow of a hot gas flowing in the hot gas path;wherein the raised geometric features comprise annular ribs oriented transverse to the direction of the flow of the cooling fluid in the cooling flow path,wherein after each time the flow of cooling fluid flows between the flow sleeve and a relatively upstream raised geometric feature, the inner surface of the flow sleeve deflects inward to direct the flow of cooling fluid toward a landing separating the relatively upstream raised geometric feature from a relatively downstream raised geometric feature,wherein the flow sleeve deflects outwards each time the flow sleeve is axially adjacent each of the raised geometric features, andwherein the inward and outward deflections repeat to form an undulation along a central axis of the hot gas path. 2. The ducting arrangement of claim 1, wherein with respect to the central axis of the hot gas path, the inner surface of the flow sleeve comprises a greater diameter when axially adjacent each relatively upstream raised geometric feature as compared to a diameter of the inner surface axially adjacent each landing separating each respective relatively upstream raised geometric feature from each relatively downstream raised geometric feature. 3. The ducting arrangement of claim 1, wherein the cooling flow path tapers outward in a direction opposite that of hot gas flowing in the hot gas path. 4. A ducting arrangement for a can annular gas turbine engine, comprising: a duct wall disposed between a combustor and a first row of turbine blades and comprising: an inner surface defining a hot gas path and an outer surface opposite the inner surface, the outer surface of the duct wall comprising raised geometric features;a flow sleeve surrounding the outer surface of the duct wall and defining a cooling flow path therebetween; anda refresher cooling hole through the flow sleeve;wherein the cooling flow path is configured to guide a flow of cooling fluid between the raised geometric features and the flow sleeve and in a direction that is counter to a direction of hot gas flowing in the hot gas path;wherein the raised geometric features protrude into the cooling flow path and comprise annular ribs oriented transverse to the direction of flow of the cooling fluid; andwherein with respect to a hot gas path central axis, a diameter of an inner surface of the flow sleeve repeatedly deflects inward and then outward to form an undulation along the hot gas path central axis, and with respect to the outer surface of the duct wall, the undulation is effective to impart an impingement vector toward the outer surface of the duct wall to the direction of flow of the cooling fluid in the cooling flow path after passing over a respective raised geometric feature,wherein with respect to the hot gas path central axis, the flow sleeve deflects outward each time the flow sleeve is axially adjacent to one of the raised geometric features and deflects inward each time the flow sleeve is axially between two adjacent raised geometric features; andwherein the refresher cooling hole is disposed in an outward deflecting portion of the undulation and is oriented to direct a flow of refresher cooling fluid toward a landing immediately following the outward deflecting portion. 5. The ducting arrangement of claim 4, wherein the undulation imparts the impingement vector to the direction of flow of the cooling fluid between all adjacent raised geometric features. 6. The ducting arrangement of claim 4, wherein for a decrease along the diameter of the outer surface of the duct wall in the direction of flow of the cooling fluid there exists a decrease in the diameter of the inner surface of the flow sleeve axially adjacent the decrease along the diameter of the outer surface of the duct wall. 7. The ducting arrangement of claim 4, wherein the inner surface of the flow sleeve comprises a corrugated curvilinear shape comprising undulations transverse to the hot gas path central axis. 8. A ducting arrangement for a can annular gas turbine engine, comprising: a duct disposed between a combustor and a first row of turbine blades, defining a hot gas path therein, and comprising raised geometric features incorporated into an outer surface;a flow sleeve defining a cooling flow path between an inner surface of the flow sleeve and the outer surface of the duct; anda refresher cooling hole through the flow sleeve;wherein the cooling flow path is configured to guide a flow of cooling fluid between the raised geometric features and the flow sleeve and in a direction that is counter to a direction of hot gas flowing in the hot gas path;wherein the raised geometric features comprise annular ribs oriented perpendicular to the direction of flow of the cooling fluid; andwherein with respect to a central axis of the hot gas path, the inner surface of the flow sleeve deflects inwards when axially adjacent each of a plurality of respective landings, each landing disposed between adjacent raised geometric features, and the inner surface of the flow sleeve deflects outwards when axially adjacent each of a plurality of the raised geometric features to form an undulation in the flow sleeve, andwherein with respect to the central axis of the hot gas path, the refresher cooling hole is disposed where the flow sleeve deflects outward over an axially adjacent and radially inward raised geometric feature of the plurality of raised geometric features, and wherein the refresher cooling hole aims toward a landing of the plurality of respective landings immediately downstream of the axially adjacent and radially inward raised geometric feature. 9. The ducting arrangement of claim 8, wherein the cooling flow path comprises a tapered shape that expands in an upstream direction of the central axis of the hot gas path. 10. The ducting arrangement of claim 8, wherein the inner surface of the flow sleeve comprises a curvilinear shape in a direction of the central axis of the hot gas path. 11. The ducting arrangement of claim 8, the flow sleeve further comprising a plurality of additional refresher cooling holes therethrough at a plurality of differing locations relative to the raised geometric features along the central axis of the hot gas path.

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이 특허를 인용한 특허 피인용횟수: 1

Mansfield-Marcoux, Danielle; Vignali, Mark. Cabin air compressor outlet duct. USP2016099440743.

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Ducting arrangement for cooling a gas turbine structure

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Ducting arrangement for cooling a gas turbine structure

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