US 9,810,099 B2
Turbine exhaust cylinder strut strip for shock induced oscillation control
Ali Akturk, Oviedo, FL (US); Jose L. Rodriguez, Lake Mary, FL (US); David L. Wasdell, Winter Park, FL (US); John A. Orosa, Palm Beach Gardens, FL (US); and Matthew D. Montgomery, Jupiter, FL (US)
Assigned to SIEMENS ENERGY, INC., Orlando, FL (US)
Filed by Siemens Energy, Inc., Orlando, FL (US)
Filed on Jun. 29, 2015, as Appl. No. 14/753,384.
Prior Publication US 2016/0376929 A1, Dec. 29, 2016
Int. Cl. F01D 25/04 (2006.01); F01D 25/30 (2006.01); F15D 1/00 (2006.01); F01D 25/16 (2006.01)
CPC F01D 25/30 (2013.01) [F01D 25/04 (2013.01); F01D 25/162 (2013.01); F15D 1/0025 (2013.01); F05D 2240/121 (2013.01); F05D 2260/964 (2013.01)] 16 Claims
OG exemplary drawing
 
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; and
a 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, and
wherein 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.
 
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, and
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.