Turbine exhaust cylinder strut strip for shock induced oscillation control
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/04
F01D-025/30
F15D-001/00
F01D-025/16
출원번호
US-0753384
(2015-06-29)
등록번호
US-9810099
(2017-11-07)
발명자
/ 주소
Akturk, Ali
Rodriguez, Jose L.
Wasdell, David L.
Orosa, John A.
Montgomery, Matthew D.
출원인 / 주소
SIEMENS ENERGY, INC.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluc
An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.
대표청구항▼
1. An arrangement to control vibrations in a gas turbine exhaust diffuser, comprising: a gas turbine exhaust diffuser, comprising: a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer conical surfa
1. An arrangement to control vibrations in a gas turbine exhaust diffuser, comprising: a gas turbine exhaust diffuser, comprising: a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer conical surface and bounded radially inward by an inner conical surface;a turbine exhaust cylinder strut comprising a turbine exhaust cylinder strut airfoil arranged in the turbine exhaust cylinder between the outer conical surface and the inner conical surface; anda protrusion disposed on the turbine exhaust cylinder strut for controlling shock induced oscillations in the gas turbine exhaust diffuser,wherein the controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced,wherein the protrusion is a rectangular strip chamfered on a corner of the rectangular strip creating an chamfered edge,wherein the chamfered edge faces the fluid flow from the leading edge of the turbine exhaust cylinder strut airfoil, andwherein a height of the rectangular strip from a hub of the turbine exhaust cylinder strut is between and 40% and 70% of the span of the turbine exhaust cylinder strut. 2. The arrangement as claimed in claim 1, wherein the protrusion is disposed on a suction side of the turbine exhaust cylinder strut airfoil. 3. The arrangement as claimed in claim 2, wherein the protrusion is disposed on the suction side of a leading edge of the turbine exhaust cylinder strut airfoil. 4. The arrangement as claimed in claim 3, wherein a distance from the leading edge of the turbine exhaust cylinder strut to a leading edge of the protrusion on the suction side is in a range from 7.5% to 12% of the strut chord length. 5. The arrangement as claimed in claim 1, wherein a chamfer angle measured from a top face of the rectangular strip to the chamfered edge is less than 30 degrees. 6. The arrangement as claimed in claim 1, wherein the rectangular strip is attached to the turbine exhaust cylinder strut by welding. 7. The arrangement as claimed in claim 6, wherein a front attachment zone comprising a weld bead is disposed on a front face of the rectangular strip such that an angle of an edge of the front attachment zone with respect to the top face is the chamfer angle, andwherein an edge of the front attachment zone and the chamfered edge of the rectangular strip form a continuous ramped front edge. 8. The arrangement as claimed in claim 6, wherein an aft attachment zone comprising a weld bead is disposed on a back face of the rectangular strip, andwherein the aft attachment zone does not extend to the top face of the rectangular strip such that a backward facing step is formed above the aft attachment zone fixing a location of fluid flow separation. 9. The arrangement as claimed in claim 1, wherein a thickness of the rectangular strip is in a range of 3% to 6% of strut maximum thickness. 10. The arrangement as claimed in claim 1, wherein a material of the protrusion is the same as a material of the turbine exhaust cylinder strut. 11. A method for controlling fluid flow induced vibrations in a gas turbine diffuser, comprising: disposing a protrusion on a turbine exhaust cylinder strut of the gas turbine exhaust diffuser;coupling the protrusion to the turbine exhaust cylinder strut,wherein the protrusion controls shock induced oscillations which minimizes pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of fluid flow surrounding the turbine exhaust cylinder strut is reduced,wherein the disposing includes positioning the protrusion on the suction side of the leading edge of a turbine exhaust cylinder strut airfoil, andwherein a distance from the leading edge of the turbine exhaust cylinder strut to a leading edge of the protrusion on the suction side is in a range from 7.5% to 12% of the strut chord length. 12. The method as claimed in claim 11, wherein the coupling includes welding the protrusion to a surface of a turbine exhaust cylinder strut. 13. The method as claimed in claim 11, wherein the protrusion is a rectangular strip chamfered on a corner of the rectangular strip creating an chamfered edge, wherein the chamfered edge faces the fluid flow from the leading edge of the turbine exhaust cylinder strut airfoil. 14. The method as claimed in claim 13, wherein the welding includes disposing a front weld bead on a front face of the rectangular strip such that an angle of an edge of the weld bead with respect to the top face is the chamfer angle, andwherein the edge of the weld bead and the chamfered edge of the rectangular strip form a continuous ramped front edge. 15. The method as claimed in claim 13, wherein the welding includes disposing an aft weld bead on a back face of the rectangular strip, andwherein the aft weld bead (370) does not extend to the top face of the rectangular strip such that a backward facing step is formed above the aft weld bead fixing a location of fluid flow separation. 16. The method as claimed in claim 13, wherein a chamfer angle measured from a top face of the rectangular strip to the chamfered edge is less than 30 degrees.
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이 특허에 인용된 특허 (5)
Steadings, Stephen W.; Buck, William C.; Barton, Christopher B., Locking chuck.
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