초록 ▼

A turbine blade with a film cooling holes arrangement to supply film cooling to hot sections on the pressure side and suction side of the blade. The cooling flow circuit for the blade uses a serpentine flow cooling path to supply cooling air to a number of impingement cavities, the impingement cavit

A turbine blade with a film cooling holes arrangement to supply film cooling to hot sections on the pressure side and suction side of the blade. The cooling flow circuit for the blade uses a serpentine flow cooling path to supply cooling air to a number of impingement cavities, the impingement cavities being connected to film cooling holes to discharge film cooling air to key spots on the pressure side wall and suction side wall of the blade that require film cooling air. The serpentine flow cooling channels are located on the opposite side of the blade from the impingement cavity in which the channel communicates with through metering and impingement holes. The first and second legs of the serpentine flow cooling channels are located on the pressure side, and the third leg or channel is located on the suction side of the blade downstream from the gage point and where no further film cooling is preferred. By moving the serpentine flow cooling supply channel from the pressure side to the suction side in the third leg, the film cooling holes on the pressure side of the blade can be supplied through metering holes and an impingement cavity that discharge the film cooling air. The remaining legs of the serpentine flow cooling supply channels are in the trailing edge region of the blade, and a plurality of exit holes discharge cooling air from the last leg of the cooling supply channels.

대표청구항 ▼

I claim: 1. A turbine blade for use in a gas turbine engine, the blade comprising: an airfoil having a pressure side and a suction side; a first row of film cooling holes located on the suction side of the blade; a first impingement cavity located to provide impingement cooling on the suction side

I claim: 1. A turbine blade for use in a gas turbine engine, the blade comprising: an airfoil having a pressure side and a suction side; a first row of film cooling holes located on the suction side of the blade; a first impingement cavity located to provide impingement cooling on the suction side wall of the blade and in fluid communication with the first row of film cooling holes; a second row of film cooling holes located on the pressure side of the blade; a second impingement cavity located to provide impingement cooling on the pressure side wall of the blade and in fluid communication with the second row of film cooling holes; a serpentine flow cooling path comprising a first cooling supply channel located on the pressure side of the blade and opposed to the first impingement cavity; a first metering and impingement hole to connect the first cooling supply channel to the first impingement cavity; the serpentine flow cooling path further comprising a second cooling supply channel located on the suction side of the blade and opposed to the second impingement cavity; and, a second metering and impingement hole to connect the second cooling supply channel to the second impingement cavity. 2. The turbine blade of claim 1, and further comprising: a third row of film cooling holes located on the suction side of the blade and downstream from the first row of film cooling holes; a third impingement cavity located to provide impingement cooling on the suction side wall of the blade and in fluid communication with the third row of film cooling holes; the serpentine flow cooling path further comprising a third cooling supply channel located on the pressure side of the blade and opposed to the third impingement cavity; and, a third metering and impingement hole to connect the third cooling supply channel to the third impingement cavity; and, the serpentine flow path flows from the first cooling supply channel, into the third channel, and then into the second channel. 3. The turbine blade of claim 2, and further comprising: each of the impingement cavities is formed from a plurality of compartments arranged substantially along a spanwise direction of the blade in parallel to the associated cooling supply channel; and, each of the compartments being in fluid communication with the respective cooling supply channel through at least one metering and impingement hole. 4. The turbine blade of claim 3, and further comprising: the serpentine flow path further comprising a fourth cooling supply channel extending along the trailing edge portion of the blade between both the pressure side and the suction side walls; and, a plurality of exit holes spaced along the trailing edge of the blade and in fluid communication with the fourth cooling supply channel. 5. The turbine blade of claim 4, and further comprising: a leading edge cooling supply channel; a leading edge cooling cavity located between the leading edge cooling channel and the leading edge of the blade; a metering hole to provide fluid communication between the leading edge cooling channel and the leading edge cooling cavity; and, a showerhead cooling arrangement with film cooling holes in the leading edge region of the blade and in fluid communication with the leading edge cooling cavity. 6. The turbine blade of claim 5, and further comprising: the leading edge cooling supply channel is separate from the serpentine flow cooling path such that the cooling air does not mix. 7. The turbine blade of claim 6, and further comprising: the pressure side channels have substantially the same blade chordwise length as the suction side channels. 8. The turbine blade of claim 1, and further comprising: each of the impingement cavities is formed from a plurality of compartments arranged substantially along a spanwise direction of the blade in parallel to the associated cooling supply channel; and, each of the compartments being in fluid communication with the respective cooling supply channel through at least one metering and impingement hole. 9. The turbine blade of claim 1, and further comprising: the serpentine flow path further comprising a fourth cooling supply channel extending along the trailing edge portion of the blade between both the pressure side and the suction side walls; and, a plurality of exit holes spaced along the trailing edge of the blade and in fluid communication with the fourth cooling supply channel. 10. The turbine blade of claim 1, and further comprising: a leading edge cooling supply channel; a leading edge cooling cavity located between the leading edge cooling channel and the leading edge of the blade; a metering hole to provide fluid communication between the leading edge cooling channel and the leading edge cooling cavity; and, a showerhead cooling arrangement with film cooling holes in the leading edge region of the blade and in fluid communication with the leading edge cooling cavity. 11. The turbine blade of claim 1, and further comprising: the pressure side channels have substantially the same blade chordwise length as the suction side channels.