IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0180578
(2011-07-12)
|
등록번호 |
US-8721291
(2014-05-13)
|
발명자
/ 주소 |
- Lee, Ching-Pang
- Tham, Kok-Mun
- Vitt, Paul H.
- Williamson, Stephen R.
- Montgomery, Matthew D.
- Prakash, Chander
- Harris, Melissa
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
12 |
초록
▼
In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending
In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.
대표청구항
▼
1. A flow directing member for a gas turbine engine, the flow directing member including a platform supported on a rotor and comprising a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall, the flow directing member furt
1. A flow directing member for a gas turbine engine, the flow directing member including a platform supported on a rotor and comprising a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall, the flow directing member further including an airfoil extending radially outwardly from the endwall and a fluid flow directing feature, the fluid flow directing feature comprising: a groove extending axially into the axial surface, the groove including a radially inner groove end and a radially outer groove end; andwherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forming an opening in the endwall for directing a cooling fluid to the endwall. 2. The flow directing member of claim 1, wherein the first and second groove walls are generally perpendicular to one another. 3. The flow directing member of claim 1, wherein the axial surface comprises a forward axial surface facing axially forwardly toward an oncoming flow of a working gas passing through the turbine engine, and including a plurality of the flow directing members located adjacent to each other, wherein each platform includes an axially extending mateface located in facing relationship to a mateface of an adjoining flow directing member to form mateface gaps, and at least a portion of the outer groove end is circumferentially located adjacent to one of the mateface gaps for effecting a flow of cooling air toward a leading edge of an airfoil on the adjoining flow directing member. 4. The flow directing member of claim 3, comprising contours on the endwall including peaks adjacent to the leading edges of the airfoils and extending along at least a portion of the endwalls adjacent to suction sides of the airfoils, and including at least one valley located along at least a portion of the endwalls adjacent to pressure sides of the airfoils, wherein the outer groove end discharges cooling air to flow between the peaks at the leading edges of the airfoils and toward the at least one valley. 5. The flow directing member of claim 1, wherein the axial surface comprises a rearward axial surface facing axially rearwardly in a downstream direction of the working gas, and including a plurality of the flow directing members located adjacent to each other, wherein each platform includes an axially extending mateface located in facing relationship to a mateface of an adjoining flow directing member to form mateface gaps, and at least a portion of the outer groove end is circumferentially located adjacent to one of the mateface gaps for effecting a flow of cooling air toward a trailing edge of an airfoil on the adjoining flow directing member. 6. The flow directing member of claim 5, comprising contours on the endwall including valleys located adjacent to the junction and extending in a region between trailing edges of the airfoils and adjacent mateface gaps, and at least a portion of the outer groove end of the groove is circumferentially located adjacent to one of the mateface gaps for effecting a flow of cooling air toward a valley on an endwall of an adjoining flow directing member. 7. The flow directing member of claim 1, wherein an axial depth of the groove increases from a circumferential location corresponding to the location of the inner groove end toward a mateface of the platform. 8. The flow directing member of claim 1, wherein the axial surface is generally perpendicular to the endwall. 9. The flow directing member of claim 8, wherein the inner groove end is located adjacent to an angel wing seal member extending axially from the axial surface. 10. The flow directing member of claim 8, wherein the fluid flow directing feature comprises a single groove per airfoil provided on the platform, the groove extending more than one quarter of a circumferential length of the platform. 11. A flow directing member for a gas turbine engine, the flow directing member including a platform supported on a rotor and comprising a radially facing endwall, a forward axial surface facing axially forwardly toward an oncoming flow of a working gas and extending radially inwardly from a forward junction with the endwall, and a rearward axial surface facing axially rearwardly in a downstream direction of the working gas and extending radially inwardly from a rearward junction with the endwall, the flow directing member further including an airfoil extending radially outwardly from the endwall, the flow directing member further comprising: a first groove defining a first fluid flow directing feature, the first groove extending axially into the forward axial surface and directing cooling fluid from a first cooling fluid cavity associated with the flow directing member;a second groove defining a second fluid flow directing feature, the second groove extending axially into the rearward axial surface and directing cooling fluid from a second cooling fluid cavity associated with the flow directing member; andat least one contour on the endwall comprising at least one of: at least one peak adjacent to a leading edge of the airfoil and extending along at least a portion of the endwall adjacent to a suction side of the airfoil; andat least one valley located along at least a portion of the endwall adjacent to a pressure side of the airfoil. 12. The flow directing member of claim 11, wherein: the first groove comprises a radially inner groove end and a radially outer groove end, the outer groove end of the first groove defining an axially extending notch in the forward junction and forming an opening in the endwall for directing cooling fluid from the first cavity to the endwall; andthe second groove including a radially inner groove end and a radially outer groove end, the outer groove end of the second groove defining an axially extending notch in the rearward junction and forming an opening in the endwall for directing cooling fluid from the second cavity to the endwall. 13. The flow directing member of claim 12, wherein the first and second grooves are each defined by respective first and second axially and radially extending groove walls that extend generally perpendicular to one another. 14. The flow directing member of claim 12, including a plurality of the flow directing members located adjacent to each other, wherein each platform includes an axially extending mateface located in facing relationship to a mateface of an adjoining flow directing member to form mateface gaps, and at least a portion of the outer groove end of the first groove is circumferentially located adjacent to one of the mateface gaps for effecting a flow of cooling air toward a leading edge of an airfoil on the adjoining flow directing member. 15. The flow directing member of claim 14, comprising contours on the endwall including peaks adjacent to the leading edges of the airfoils and extending along at least a portion of the endwalls adjacent to suction sides of the airfoils, and including at least one valley located along at least a portion of the endwalls adjacent to pressure sides of the airfoils, wherein the outer groove end of the first groove discharges cooling air to flow between the peaks at the leading edges of the airfoils and toward the at least one valley. 16. The flow directing member of claim 15, wherein the contours further include valleys located adjacent to the rearward junction and extending in a region between trailing edges of the airfoils and adjacent mateface gaps, and at least a portion of the outer groove end of the second groove is circumferentially located adjacent to one of the mateface gaps for effecting a flow of cooling air toward a valley on an endwall of an adjoining flow directing member. 17. The flow directing member of claim 12, wherein the cooling fluid directed by the first groove includes a component in a first direction that is parallel to a direction of rotation of the rotor, and the cooling fluid directed by the second groove includes a component in a second direction opposite to the first direction. 18. The flow directing member of claim 12, wherein the flow directing member comprises a single first groove per airfoil provided on the platform and a single second groove per airfoil provided on the platform, the first and second grooves each extending more than one quarter of a circumferential length of the platform.
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