Abstract: An assembly is provided with a housing, a guide sleeve, and a spring. The guide sleeve may be at least partially housed within the housing. The spring may be disposed to abut against the housing and the guide sleeve.

Abstract: An assembly is provided with a housing, a guide sleeve, and a spring. The guide sleeve may be at least partially housed within the housing. The spring may be disposed to abut against the housing and the guide sleeve.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A method of measuring a gas turbine engine operating parameter is provided. The method includes providing at least one engine component and a plurality of sensors, positioning each of the plurality of sensors relative to an index location, defining a periodic gas flow operating parameter distribution profile to extend across an engine component or between engine components, obtaining a gas flow operating parameter reading from each of the plurality of sensors, and determining at least one operating parameter for defining a periodic gas flow operating parameter distribution.

Abstract: A method for determining sensor locations in a gas turbine engine is provided. The said method includes providing a turbine rear frame including a radially inner surface, a radially outer surface and a plurality of circumferentially-spaced struts extending between the inner and outer surfaces, wherein a strut sector is defined between each pair of circumferentially-adjacent struts, providing a plurality of fuel nozzles that are each aligned with a strut sector, selecting one of the plurality of fuel nozzles as a primary index nozzle and positioning each of a plurality of sensors relative to one of the plurality of nozzles using a corresponding positioning angle such that each of the plurality of sensors coincides with a gas flow temperature distribution profile between each pair of circumferentially-spaced nozzles.

Abstract: A method of measuring a gas turbine engine operating parameter is provided. The method includes providing at least one engine component and a plurality of sensors, positioning each of the plurality of sensors relative to an index location, defining a periodic gas flow operating parameter distribution profile to extend across an engine component or between engine components, obtaining a gas flow operating parameter reading from each of the plurality of sensors, and determining at least one operating parameter for defining a periodic gas flow operating parameter distribution.

Abstract: A system for detecting spark in an igniter for a gas turbine engine. An igniter generates a plasma, or spark, somewhat similar to an automotive spark plug. In the invention, an inductive pick-up is positioned adjacent the igniter, to detect current pulses in the igniter, to thereby infer the presence of spark. A detection system detects the spark, and informs the pilot of the aircraft of the detected spark. Thus, if the pilot encounters a problem in starting the engine, the pilot can rapidly determine whether the igniter is involved in the problem.

Abstract: A method for testing an igniter coupled within a gas turbine engine, wherein the gas turbine engine includes a combustor, a pressure transducer coupled to the combustor, and a spark detector. The method includes operating the gas turbine engine, monitoring the operating pressure within the gas turbine engine, operating the igniter when the monitored pressure is within a first predefined pressure range, and generating a first indication if the igniter failed to generate a spark within the first predefined pressure range.

Abstract: A vane assembly includes a vane having a main axis, a first passageway within the vane substantially parallel to the main axis, and a second passageway aligned with the first passageway. The vane has a window portion between the first passageway and the second passageway. The vane assembly also includes a sensor inserted in the first passageway and having a portion held in place in the second passageway, wherein a portion of the sensor is exposed in the window portion of the vane.