Abstract: A system and method of increasing the temperature of oil that is used to anti-ice a gas turbine propulsion engine includes supplying oil from an oil supply system to an anti-ice oil circulation system that is disposed within the front frame of the gas turbine propulsion engine, and selectively injecting compressed air from the gas turbine propulsion engine into the oil supply system.

Abstract: An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured to selectively receive a flow of compressed air that is discharged from the compressor. Because the compressed air is relatively hot, the anti-ice formation device temperature increases to a temperature sufficient to prevent ice accumulation and formation in the engine inlet duct. The anti-ice formation device is also configured such that heat is not transferred to the compressor inlet housing. As a result, the anti-ice formation device does not cause impeller clearance variations, which would adversely affect engine performance.

Abstract: A system and method for readily generating radial clearance data for a radial clearance between locations on at least two parts in a rotating machine includes rendering an image of a cross section view of at least a portion of the machine on a display. The locations on the two parts are identified on the rendered cross section, and a radial stack path between the identified locations is automatically determined. The radial clearance between the identified locations when the machine is not operating is determined, based at least in part on the determined radial stack path. Data generated by a deflection analysis model of the machine are used to determine radial deflections of the identified locations during machine operation at one or more machine operating conditions. Data representative of the radial clearance between the identified locations during the machine operation at the one or more machine operating conditions are generated.

Abstract: An anti-ice formation device for a gas turbine engine is configured to be mounted within an inlet duct of the engine, and adjacent the gas turbine engine compressor inlet. The device is configured to selectively receive a flow of compressed air that is discharged from the compressor. Because the compressed air is relatively hot, the anti-ice formation device temperature increases to a temperature sufficient to prevent ice accumulation and formation in the engine inlet duct. The anti-ice formation device is also configured such that heat is not transferred to the compressor inlet housing. As a result, the anti-ice formation device does not cause impeller clearance variations, which would adversely affect engine performance.

Abstract: A system and method for readily generating radial clearance data for a radial clearance between locations on at least two parts in a rotating machine includes rendering an image of a cross section view of at least a portion of the machine on a display. The locations on the two parts are identified on the rendered cross section, and a radial stack path between the identified locations is automatically determined. The radial clearance between the identified locations when the machine is not operating is determined, based at least in part on the determined radial stack path. Data generated by a deflection analysis model of the machine are used to determine radial deflections of the identified locations during machine operation at one or more machine operating conditions. Data representative of the radial clearance between the identified locations during the machine operation at the one or more machine operating conditions are generated.