Cooled vane for a gas turbine engine

Details Cooled vane for a gas turbine engine Cooled vane for a gas turbine engine

1982-02-24

1984-03-20

Coe, Philip R.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

416 96A, 416 97R, F01D 518

Patent

active

044378106

ABSTRACT:
A cooled vane for a gas turbine engine has a hollow aerofoil with apertures at its trailing edge for cooling air ejection. In order to control the flow of cooling air out of these apertures a metering insert extends between the opposed internal faces of the aerofoil adjacent the trailing edge and accurately defines the required flow areas.
In a preferred embodiment the insert is of `hairpin` cross section and defines the flow area as channels between projections from the limbs of the `hairpin` which abut with the internal faces of the aerofoil. A cooling air entry tube then engages with the concavity of the hairpin, and the flow down the two flanks of the tube may be controlled by the flow area provided by the projections on the respective limb.

REFERENCES:
patent: 3767322 (1973-10-01), Durgin et al.
patent: 4025226 (1977-05-01), Hovan
patent: 4056332 (1977-11-01), Meloni
patent: 4252501 (1981-02-01), Peill
patent: 4257734 (1981-03-01), Guy et al.

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