Patent ID: 7410343

Claim:
A gas turbine comprising: moving blades attached to a rotor; an exhaust diffuser comprising a strut main body configured to support the rotor provided therein, the exhaust diffuser being configured to take up combustion gas at an exit of the moving blades to recover pressure; and a strut cover configured to protect the strut main body from the combustion gas and to reduce shock formation in a trailing edge region of said strut cover, wherein an outer shape of a section in the longitudinal direction at a leading edge of the strut cover is elliptical in shape and whose thickness gradually increases initially along a flow direction of the combustion gas, and a Mach number ratio has a peak approximately 2.2 at 11% distance from the leading edge (LE 1 ), and is approximately 1.7 at 27% distance from the leading edge (LE 1 ), under the conditions that distance from the leading edge (LE 1 ) is indicated in percentage with reference to the length (L) of the strut cover, and speed of the combustion gas flowing along the strut cover is indicated as Mach number ratio with reference to a speed of the combustion gas at the trailing edge (TE 1 ).