Chordally bifurcated turbine blade

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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F01D 518

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active

053562658

ABSTRACT:
A gas turbine engine turbine blade includes an airfoil having pressure and suction sides joined together at leading and trailing edges and extending from a root to a tip. The airfoil also includes a longitudinally extending flow channel for receiving compressed air, with the flow channel including a chordally extending, imperforate septum dividing the flow channel into first and second laterally spaced apart flow chambers. The blade further includes a supply manifold for receiving the compressed air at a single pressure which is disposed in flow communication with both the first and second chambers for channeling thereto respective first and second portions of the compressed air. The septum is used to reduce or eliminate radial velocity distortion, or blowoff of film cooling air from the suction side.

REFERENCES:
patent: 3533711 (1970-10-01), Kercher
patent: 3542486 (1970-11-01), Kercher et al.
patent: 3801218 (1974-04-01), Moore
patent: 4063851 (1977-12-01), Weldon
patent: 4118146 (1978-10-01), Dierberger
patent: 4135855 (1979-01-01), Peill
patent: 4224011 (1980-09-01), Dodd et al.
patent: 4601638 (1986-07-01), Hill et al.
patent: 4940388 (1990-07-01), Lilleker et al.
Haerter, "Flow Distribution and Pressure Change Along Slotfed or Branched Ducts," 11-14 Feb. 1963, Ashrae Journal, pp. 47 & 50.
Genium Publishing, "Supply Manifold Used with a Matrix Having Unrestricted, Undeflected Discharge Flow," Aug. 1974, Branching Flow Manifolds Section 404.3, p. 5.
Japanese Patent 19959, dated Feb. 1980, abstract only.

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