Turbine blade and turbine with improved sealing
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/12
F01D-005/14
F01D-005/08
F01D-011/00
출원번호
US-0336152
(2014-07-21)
등록번호
US-9816393
(2017-11-14)
우선권정보
EP-13178679 (2013-07-31)
발명자
/ 주소
Simon-Delgado, Carlos
Didion, Christoph
Biedermann, Stefan
Von Arx, Beat
Zierer, Thomas
출원인 / 주소
ANSALDO ENERGIA IP UK LIMITED
대리인 / 주소
Buchanan Ingersoll & Rooney PC
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section
The disclosure pertains to a turbine with a gas turbine blade and a rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine. The rotor heat shield includes a platform which forms an axial heat shield section and which is arranged substantially parallel to the surface of a rotor and a radial heat shield section at the upstream end of the axial heat shield section, which is extending in a direction away from the surface of the axial heat shield section towards the hot gas. Further the turbine comprises a blade rear cavity which is delimited by the downstream end of the platform and/or the downstream end of the blade foot, the radial heat shield section. The disclosure further refers to a gas turbine blade and a rotor heat shield designed for such a turbine.
대표청구항▼
1. A gas turbine blade comprising: a blade platform having a trailing edge side, a pressure side, a suction side, and a leading edge side;an airfoil connected to the blade platform, anda first groove formed in the trailing edge side of the platform, wherein the first groove extends between the press
1. A gas turbine blade comprising: a blade platform having a trailing edge side, a pressure side, a suction side, and a leading edge side;an airfoil connected to the blade platform, anda first groove formed in the trailing edge side of the platform, wherein the first groove extends between the pressure side and the suction side, and wherein the first groove extends in an axial direction below a root of a trailing edge of the airfoil, the first groove configured so that the trailing edge side of the blade platform is not rigidly connected to a foot of a blade,a trailing edge side seal groove formed in the trailing edge side of the blade platform closer to a platform surface of the blade platform facing the airfoil than the first groove, wherein the trailing edge side seal groove extends between the pressure side and the suction side, and wherein a depth of the trailing edge side seal groove in axial direction is smaller than a depth of the first groove;a main seal above the first groove; anda rear seal positioned adjacent the first groove below the trailing edge side seal groove, the rear seal extending radially from the main seal to the foot of the blade to control leakage from the blade to a heat shield cavity of a heat shield downstream of the blade;an upper seal above the first groove, a portion of the upper seal positioned in the trailing edge side seal groove of the blade platform; anda lower seal below the first groove that extends between the foot and the heat shield to separate a blade rear cavity from the heat shield cavity. 2. The gas turbine blade according to claim 1, wherein the first groove has an axial depth that enters into a line of stress created by a blade load. 3. The gas turbine blade according to claim 1, wherein the trailing edge side seal groove is configured to hold a strip seal. 4. The gas turbine blade according to claim 1, wherein the blade comprises a seal groove extending to the trailing edge of the blade platform on the pressure side of the blade platform and/or on the suction side of the blade platform for receiving the main seal above the first groove. 5. The gas turbine blade according to claim 1, wherein the blade comprises a seal groove on the pressure side of the platform and/or on the suction side of the platform for receiving the rear seal extending radially inwardly below the first groove. 6. A gas turbine rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of a gas turbine through which coolant flows, comprising: a platform which forms an axial heat shield section and which is arranged substantially parallel to a surface of a rotor,wherein the rotor heat shield includes a radial heat shield section arranged at one end of an axial heat shield section, the radial heat shield section extending radially in a direction away from a surface of the axial heat shield section towards a hot gas side of the heat shield;a first end of the radial heat shield section being adjacent an upper seal extending between the rotor heat shield and a blade platform;a second end of the radial heat shield section being adjacent the axial heat shield section;a blade rear cavity being defined between the radial heat shield section, the upper seal, and the blade platform such that a heat shield cavity of the rotor heat shield and the blade rear cavity are independently suppliable with coolant; anda lower seal that separates the heat shield cavity from the blade rear cavity below the upper seal. 7. The gas turbine rotor heat shield according to claim 6, wherein the radial heat shield section is extending at an angle of more than 30° in a direction away from the surface of the axial heat shield section towards the hot gas side. 8. The gas turbine rotor heat shield according to claim 6, wherein the radial heat shield section comprises a kink to bridge a gap between the blade platform and the rotor heat shield for holding the upper seal. 9. A turbine comprising: a blade comprising: a blade platform having a trailing edge side, a pressure side, a suction side, and a leading edge side;an airfoil connected to the blade platform, anda first groove formed in the trailing edge side of the blade platform, wherein the first groove extends between the pressure side and the suction side and wherein the first groove extends in an axial direction below a trailing edge of the airfoil, anda rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine, wherein the rotor heat shield comprises an axial heat shield section which is arranged substantially parallel to a surface of a rotor of the rotor arrangement, wherein the rotor heat shield comprises a radial heat shield section at an upstream end of the axial heat shield section, the radial heat shield section extending in a direction away from a surface of the axial heat shield section towards a hot gas side of the rotor heat shield such that a blade rear cavity is defined between the radial heat shield section and at least one of the blade platform and a foot of the blade;a main seal above the first groove and above the blade rear cavity;a rear seal positioned adjacent the first groove, the rear seal extending radially from the main seal toward the foot of the blade to control leakage from the blade to a heat shield cavity of the rotor heat shield downstream of the blade; anda lower seal arranged between the radial heat shield section and the rear seal below the blade rear cavity for separating the blade rear cavity from the heat shield cavity. 10. The turbine according to claim 9, wherein the blade comprises a trailing edge side seal groove formed in the trailing edge side of the blade platform closer to a platform surface facing the airfoil than the first groove, wherein the trailing edge side seal groove extends between the pressure side and the suction side, and wherein the depth of the trailing edge side seal groove in axial direction is smaller than the depth of the first groove. 11. The turbine according to claim 10, wherein the turbine comprises an upper seal arranged between the trailing edge side seal groove and the radial heat shield section. 12. The turbine according to claim 9, wherein the blade comprises a seal groove for receiving the rear seal on the pressure side of the blade platform and/or on the suction side of the blade platform, the rear seal extending radially inwardly below the first groove for sealing a space formed between adjacent blades of one turbine row at a downstream end towards the blade rear cavity. 13. A turbine comprising: a blade comprising: a blade platform having a trailing edge side, a pressure side, a suction side, and a leading edge side;an airfoil connected to the blade platform, anda first groove formed in the trailing edge side of the blade platform, wherein the first groove extends between the pressure side and the suction side and wherein the first groove extends in an axial direction below a trailing edge of the airfoil, anda rotor heat shield for separating a space region through which hot working medium flows from a space region inside a rotor arrangement of the turbine, wherein the rotor heat shield comprises an axial heat shield section which is arranged substantially parallel to a surface of a rotor of the rotor arrangement, wherein the rotor heat shield comprises a radial heat shield section at an upstream end of the axial heat shield section, the radial heat shield section extending in a direction away from a surface of the axial heat shield section towards a hot gas side of the rotor heat shield such that a blade rear cavity is defined between the radial heat shield section and at least one of the blade platform and a foot of the blade;a main seal above the first groove and above the blade rear cavity; anda rear seal positioned adjacent the first groove, the rear seal extending radially from the main seal toward the foot of the blade to control leakage from the blade to a heat shield cavity of the rotor heat shield downstream of the blade; anda lower seal below the first groove that extends between the foot of the blade and the heat shield to separate the blade rear cavity from the heat shield cavity. 14. The turbine of claim 13, wherein the radial heat shield section comprises a kink to bridge a gap between the blade platform and the rotor heat shield for holding an upper seal positioned above the first groove, the radial heat shield, and the lower seal between the blade platform and the rotor heat shield. 15. The turbine of claim 13, comprising: an upper seal above the lower seal, the first groove, and the blade rear cavity, the upper seal extending from the blade platform to the rotor heat shield. 16. The turbine of claim 13, wherein the lower seal is configured so that coolant is independently suppliable to the heat shield cavity and the blade rear cavity. 17. The turbine of claim 13, wherein the hot gas side of the rotor heat shield is a side of the rotor heat shield that is closest to the space region through which the hot working medium flows.
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이 특허에 인용된 특허 (8)
Mori Masahiko,JPX ; Hashimoto Yukihiro,JPX ; Tada Hiroji,JPX ; Fukue Ichiro,JPX ; Tsukagoshi Keizo,JPX ; Masada Jyunichiro,JPX, Gas turbine moving blade.
Markowski Stanley J. (East Hartford CT) Reilly Richard S. (East Hartford CT), Turbofan engine with augmented combustion chamber using vorbix principle.
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