General Electric Company

Dana D Freberg

William R Spencer

Joseph P Smith, Jr

Robert L Mentzer

A temperature sensor, for measuring the temperature of air flowing in a substantially annular path into a compressor stage of a gas turbine engine, is positioned in proximity to the inner diameter of the annular flow path forward of the compressor stage where the measured temperature of the compressor inlet air is reliable during periods of water ingestion as well as during dry operation.

Turbomachine airflow temperature sensor

The apparatus includes a first connecting link having a pair of axially opposing ends with one of the ends being coupled through a uniball to a drive portion of an actuator. A second connecting link includes a pair of axially opposing ends. One of the ends of the second connecting link is coupled to a driven portion, e.g., a butterfly valve. Coupling means, including a mating plug and socket, is provided for adjustably coupling the remaining opposing ends of the first and second links. The mating plug includes four sides and one hole disposed eccentrically therethrough and parallel to the sides. The remaining end of the second link includes a socket for mating with the plug. The plug can be mated in eight different rotational positions with respect to the socket. At each of the eight different rotational positions, the eccentric hole is disposed in a position which determines one of a predetermined number of available couplings between the first and second links. The remaining end of the first link includes an opening therethrough for receiving securing means. Securing means in the form of a bolt, including a uniball portion, passes through the eccentric hole and the opening in the first link for operationally securing the first and second links together in one of the predetermined number of couplings. Other embodiments are disclosed.

Adjustable connecting apparatus

A timing valve is responsive to certain hydraulic rotor speed input signals so as to schedule increased temperatures of air to a turbine shroud support in accordance with the thermal time constants of the rotor. Clearance between the rotor and the shroud is thereby minimized during both transient and steady-state operating conditions. Temperatures are incrementally increased by selectively combining air from the compressor fifth and ninth stage bleed manifolds. Under certain operating conditions, the timing valve is pre-empted and air is provided at a predetermined temperature level as a function of rotor speed only.

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Middletown, OH, United States of America

Dana D Freberg