Turbine blade composite cooling circuit

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

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415115, F01D 508

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active

053870859

ABSTRACT:
A gas turbine engine airfoil includes a serpentine cooling circuit with a branch cooling circuit disposed in parallel therewith for independently controlling discharge of cooling air therefrom through respective discharge holes in pressure and suction sides of the airfoil. Metering orifices are provided between the serpentine circuit and the branch circuit for controlling flow of cooling air into the branch circuit from the serpentine circuit, and therefore controlling discharge of the cooling air from the branch discharge holes relative to the serpentine discharge holes.

REFERENCES:
patent: 3656863 (1972-04-01), DeFeo
patent: 4073599 (1978-02-01), Allen et al.
patent: 4616976 (1986-10-01), Lings et al.
patent: 4770608 (1988-09-01), Anderson et al.
patent: 4992026 (1991-02-01), Ohtomo et al.
patent: 5215431 (1993-06-01), Derrien
patent: 5246340 (1993-09-01), Winstanley et al.
U.S. patent application Ser. No. 07/935,061, filed Aug. 25, 1992, D. Kercher.

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