Abstract: Method for controlling the clearance between rotating and stationary components of a gas turbine engine are disclosed. Techniques for achieving close correspondence between the radial position of rotor blade tips and the circumscribing outer air seals are disclosed. In one embodiment turbine case temperature modifying air is provided in flow rate, pressure and temperature varied as a function of engine operating condition. The modifying air is scheduled from a modulating and mixing valve supplied with dual source compressor air. One source supplies relatively low pressure, low temperature air and the other source supplies relatively high pressure, high temperature air. After the air has been used for the active clearance control (cooling the high pressure turbine case) it is then used for cooling the structure that supports the outer air seal and other high pressure turbine component parts.

Abstract: A gas turbine engine and structure for mounting the gas turbine engine on an aircraft is disclosed. Techniques for controlling the magnitude of engine case deflection from the axis of the engine are developed. The transfer of a portion of the gust and thrust loads externally of the engine case to a location downstream of the rearward engine mount generates a reverse moment which counteracts deflection in the engine case.

Abstract: The pilot burner for a high M.sub.N inlet burner is folded to substantially reduce the overall length of the combustor. The annular burner includes a splitter design where a diffuser surrounds the burner and connects to an outer shroud which contains the inlet of the pilot burner. Flow reverses into the pilot burner where it is directed to the primary burning zone of the combustion chamber.

Abstract: This invention is for a turbine type power plant which includes a swirl-type annular burner and is concerned with diverting a portion of compressor air from the compressor discharge flow stream where it is utilized for cooling and dilution in the burner and is particularly concerned with the construction of the diffuser section.

Abstract: An annular pilot combustor for a turbine type power plant includes radial inflow air and fuel nozzles judiciously oriented to improve heat load characteristics, eliminate a diffuser passage and shorten the overall combustor and supporting parts.

Abstract: A radial deflecting support member interposed between the damper support and the thrust bearing transmits the thrust loads and permits the use of an oil damper in a thrust loaded environment. The radial deflecting support has a spring rate that is at least equal to or lower than the damper support, so that when the radial deflecting support bottoms out the radial load will be absorbed by the damper support.