Gas turbine and gas turbine blade

Rotary kinetic fluid motors or pumps – With passage in blade – vane – shaft or rotary distributor...

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Details

416 97R, 416223A, F01D 518, F01D 902

Patent

active

053931980

ABSTRACT:
A blade for a gas turbine has a leading edge portion which has an arc-shaped cross-section, and a maximum thickness portion of the blade is located within this arc. With this blade configuration, an abrupt acceleration of hot gas at the leading edge portion of the blade is restrained, so that the velocity of the hot gas at the blade surface can be made low. Therefore, the heat transfer coefficient from the hot gas to the blade wall is lowered, so that the amount of cooling air required to be passed through the interior of the blade can be reduced.

REFERENCES:
patent: 1777098 (1930-09-01), Lysholm
patent: 2830753 (1958-04-01), Stalker
patent: 2866618 (1958-12-01), Jackson
patent: 3623318 (1971-11-01), Shank
patent: 4229140 (1980-10-01), Scott
patent: 4396349 (1983-08-01), Hueber
patent: 4484859 (1984-11-01), Pask et al.
patent: 4962640 (1990-10-01), Tobery
Nagai, Mori, Hiura, Sato & Fukue, (Mitsubishi), "Development of 10 MW Class Small Scale High Temperature Gas Turbine", Thermal or Nuclear Power Generation, vol. 38, No. 9, pp. 889, Fig. 15.
Transactions of the ASME Journal of Engineering for Power, Jan., 1981, vol. 103, "Boundary Layer Studies on Highly Loaded Cascades Using Heated Thin Films and a Traversing Probe", pp. 237-246.

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