Turbine rotor blade for gas turbine engine

Details Turbine rotor blade for gas turbine engine Turbine rotor blade for gas turbine engine

2007-05-15

2007-05-15

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Radial flow devices

C416S242000, C416SDIG004

Reexamination Certificate

active

10963791

ABSTRACT:
A rotor blade for a gas turbine engine includes a blade root (3) and an aerofoil projecting therefrom, the aerofoil having a leading edge and a trailing edge (5), a generally concave pressure surface (2) and a generally convex suction surface (1). The aerofoil shape of the blade varies in section along the length thereof such that:the chord-wise convex curvature of the rear suction surface decreases towards the tip (4) of the blade;the convex curvature of the early to mid suction surface increases towards the tip;the stagger of the aerofoil section increases towards the tip; andthe trailing edge (5) is a straight line.

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Search Report from GB 0324203.9 (Feb. 25, 2004).
Cohen, H., Rogers G.F.C., Saravanamuttoo H.I.H. “Gas Turbine Theory: 2ndedition”, pp. 232-235. (Longman Group Limited, 1972, Essex, U.K.).
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Staubach, J.Brent et al. “Reduction of tip clearance losses through 3-D airfoil designs.”, 12 pp, ASME 96-TA-13, Nov. 1998.

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