Internal cooling system with insert forming nearwall cooling channels in an aft cooling cavity of an airfoil usable in a gas turbine engine
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/18
출원번호
US-0505218
(2014-09-04)
등록번호
US-9863256
(2018-01-09)
국제출원번호
PCT/US2014/053968
(2014-09-04)
국제공개번호
WO2016/036366
(2016-03-10)
발명자
/ 주소
Lee, Ching-Pang
Um, Jae Y.
Pu, Zhengxiang
Abdullah, Mohamed
Schroeder, Eric
Waywood, Anthony
출원인 / 주소
SIEMENS AKTIENGESELLSCHAFT
인용정보
피인용 횟수 :
0인용 특허 :
22
초록▼
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of c
An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers (22) may be positioned within a pressure side nearwall cooling channel (48) and a suction side nearwall cooling channel (50) that are both in fluid communication with a trailing edge channel (30). The trailing edge channel (30) may also include cooling fluid flow controllers (22) extending between the outer walls (12, 13) forming the pressure and suction sides.
대표청구항▼
1. A turbine airfoil for a gas turbine engine, comprising: a generally elongated hollow airfoil formed from an outer wall and having a leading edge, a trailing edge, a pressure side, a suction side, and inner endwall at a first end and an outer endwall at a second end that is generally on an opposit
1. A turbine airfoil for a gas turbine engine, comprising: a generally elongated hollow airfoil formed from an outer wall and having a leading edge, a trailing edge, a pressure side, a suction side, and inner endwall at a first end and an outer endwall at a second end that is generally on an opposite side of the generally elongated hollow airfoil from the first end and a cooling system positioned within interior aspects of the generally elongated hollow airfoil;the cooling system includes at least one aft cooling cavity in which an insert is positioned that forms a pressure side nearwall cooling channel and a suction side nearwall cooling channel;wherein a plurality of cooling fluid flow controllers extend from the outer wall forming the generally elongated hollow airfoil toward the insert, where the cooling fluid flow controllers form a plurality of alternating zigzag channels extending downstream toward the trailing edge; andat least one bypass flow reducer extending from the insert toward the outer wall to reduce bypass flow of cooling fluids. 2. The turbine airfoil of claim 1, wherein at least one of the cooling fluid flow controllers has a cross-sectional area formed by a pressure side that is on an opposite side from a suction side, whereby the pressure and suction sides are coupled together via a leading edge and trailing edge on an opposite end of the at least one cooling fluid flow controller from the leading edge and wherein the pressure side has a generally concave curved surface and the suction side has a generally convex curved surface. 3. The turbine airfoil of claim 2, wherein the plurality of cooling fluid flow controllers are collected into a first spanwise extending row of cooling fluid flow controllers, wherein each of the cooling fluid flow controllers within the first spanwise extending row of cooling fluid flow controllers is positioned similarly, such that a pressure side of one cooling fluid flow controller is adjacent to a suction side of an adjacent cooling fluid flow controller, except for a cooling fluid flow controller at an end of the first spanwise extending row. 4. The turbine airfoil of claim 3, further wherein a second spanwise extending row of cooling fluid flow controllers positioned downstream from the first spanwise extending row of cooling fluid flow controllers. 5. The turbine airfoil of claim 4, wherein the second spanwise extending row of cooling fluid flow controllers has at least one cooling fluid flow controller with a pressure side on an opposite side of the cooling fluid flow controller than in the first spanwise extending row of cooling fluid flow controllers, thereby causing cooling fluid flowing through the second spanwise extending row of cooling fluid flow controllers to be directed downstream with a spanwise vector that is opposite to a spanwise vector imparted on the cooling fluid by the first spanwise extending row of cooling fluid flow controllers. 6. The turbine airfoil of claim 5, wherein each of the cooling fluid flow controllers forming the second spanwise extending row of cooling fluid flow controllers has at least one cooling fluid flow controller with a pressure side on an opposite side of the cooling fluid flow controller than in the first spanwise extending row of cooling fluid flow controllers. 7. The turbine airfoil of claim 1, wherein the plurality of cooling fluid flow controllers extend from the outer wall forming the pressure side of the generally elongated hollow airfoil, and wherein the plurality of cooling fluid flow controllers extend from the outer wall forming the suction side of the generally elongated hollow airfoil. 8. The turbine airfoil of claim 1, wherein both the pressure side nearwall cooling channel and the suction side nearwall cooling channel are in fluid communication with a trailing edge channel. 9. The turbine airfoil of claim 8, wherein the trailing edge channel includes a plurality of cooling fluid flow controllers extending from the outer wall forming the pressure side to the outer wall forming the suction side, wherein the cooling fluid flow controllers form a plurality of alternating zigzag channels. 10. The turbine airfoil of claim 9, wherein the plurality of cooling fluid flow controllers are collected into a first spanwise extending row of cooling fluid flow controllers, wherein each of the cooling fluid flow controllers within the first spanwise extending row of cooling fluid flow controllers is positioned similarly, such that a pressure side of one cooling fluid flow controller is adjacent to a suction side of an adjacent cooling fluid flow controller, except for a cooling fluid flow controller at an end of the first spanwise extending row, and further comprising a second spanwise extending row of cooling fluid flow controllers positioned downstream from the first spanwise extending row of cooling fluid flow controllers, wherein the second spanwise extending row of cooling fluid flow controllers has at least one cooling fluid flow controller with a pressure side on an opposite side of the cooling fluid flow controller than in the first spanwise extending row of cooling fluid flow controllers, thereby causing cooling fluid flowing through the second spanwise extending row of cooling fluid flow controllers to be directed downstream with a spanwise vector that is opposite to a spanwise vector imparted on the cooling fluid by the first spanwise extending row of cooling fluid flow controllers. 11. The turbine airfoil of claim 8, wherein the insert includes at least one refresher hole to supply the trailing edge channel in addition to the pressure side nearwall cooling channel and the suction side nearwall cooling channel. 12. The turbine airfoil of claim 1, wherein the insert in the at least one aft cooling cavity includes at least one inlet in fluid communication with a cooling fluid supply positioned in an inner diameter of the generally elongated hollow airfoil.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (22)
Downs, James P; Fedock, John A, Air cooled turbine airfoil with sequential impingement cooling.
Flodman, David Allen; Shapiro, Jason David; Manning, Robert Francis; Gledhill, Mark Douglas; Hooper, Tyler Frederick, Hybrid impingement cooled airfoil.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.