FIELD: blades for aircraft engines.
SUBSTANCE: proposed blade is provided with at least three cooling circuits. First cooling circuit has at least one cavity on concave end of blade feather stretched in radial direction close to concave surface of feather. Second cooling circuit is independent of first one and has at least one cavity on convex end of feather stretched in radial direction near convex surface of feather. Third cooling circuit is independent of first and second ones and has at least one central cavity disposed in central part of blade feather between cavity on concave end of feather and that on its convex part, at least one cavity near entrance edge of feather, inlet holes providing communication between central part and cavity near entrance edge of feather, as well as outlet holes communicating with mentioned cavity near entrance edge of feather and with entrance edge of feather.
EFFECT: reduced temperature of blade feather entrance edge.
10 cl, 5 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| GAS-TURBINE BLADE PROVIDED WITH COOLING CIRCUITS | 2002 |
|
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RU2489573C2 |
