Adaptable articulating axial-flow compressor/turbine rotor blade

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United States of America Patent

PATENT NO 11073160
APP PUB NO 20180066671A1
SERIAL NO

15691858

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Abstract

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Conventional gas turbine engines are generally optimized to operate at nearly a fixed speed with fixed blade geometries for the design operating condition. When the operating condition of the engine changes, the flow incidence angles may not be optimum with the blade geometries resulting in reduced off-design performance. By contrast, according to embodiments of the present invention, articulating the pitch angle of turbine blades in coordination with adjustable nozzle vanes improves performance by maintaining flow incidence angles within the optimum range at all operating conditions of a gas turbine engine. Maintaining flow incidence angles within the optimum range can prevent the likelihood of flow separation in the blade passage and also reduce the thermal stresses developed due to aerothermal loads for variable speed gas turbine applications.

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Patent Owner(s)

  • THE UNITED STATES OF AMERICA AS REPRESENTED BY THE SECRETARY OF THE ARMY

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Bravo, Luis Bel Air, US 1 12
Ghoshal, Anindya Phoenix, US 7 115
Murugan, Muthuvel Abingdon, US 2 12

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