Abstract: The turbine blade tip clearance control system presently used with existing turbine blade uses an abradable seal material with a conventional squealer tip. Others use a thin, coating added to the tip of the blade. The present turbine blade tip control system minimizes the problem of controlling the clearance between the blade and the shroud and overcomes the problem of wearing away of the thin coating added to the tip by using a rub tolerant, high-temperature seal material coating on a turbine shroud and a turbine blade made of at least two materials. The combination of the coating and an outer tip being of a different material than the metallic body also minimizes the problems associated with the burning of dirty fuels. The blade has a metallic body of high strength and the outer tip has a strength less than the strength of the body and made of a material resistant to oxidation, sulfidation and thermal fatigue at operating temperatures. The outer tip has a radial length "L" at least 1 mm in length.

Abstract: A metallic gasket for sealing a joint between first and second surfaces subjected to high pressure and high temperature. Other gaskets used to seal such joints are of a fibrous composition held together by a suitable bonding agent and a deformable elastomer coat or bead. Many of these gaskets used for high pressure and high temperature use an asbestos sheet which is regarded as toxic and unsafe to handle. The present gasket is comprised of a substantially non-compressible sheet and pair of seals made from a ductile material connected to opposite sides of the sheet. The sheet and seals are positioned between the surfaces to be sealed and the seals conform to the surface finish topography of the surfaces when a predetermined compressive load is applied between the surfaces resulting in a positive sealed joint suitable for high pressure and high temperature.

Abstract: The turbine blade tip clearance control system presently used with existing turbine blade uses an abradable seal material with a conventional squealer tip. Others use a thin, coating added to the tip of the blade. The present turbine blade tip control system minimizes the problem of controlling the clearance between the blade and the shroud and ovecomes the problem of wearing away of the thin coating added to the tip by using a rub tolerant, high-temperature seal material coating on a turbine shroud and a turbine blade made of at least two materials. The combination of the coating and an outer tip being of a different material than the metallic body also minimizes the problems associated with the burning of dirty fuels. The blade has a metallic body of high strength and the outer tip has a strength less than the strength of the body and made of a material resistant to oxidation, sulfidation and thermal fatigue at operating temperatures. The outer tip has a radial length "L" at least 1 mm in length.

Abstract: Cooling air delivery systems for gas turbine engines are used to increase component life and increase efficiencies. To change the flow rate of cooling air in past engines, major disassembly of engine components was required resulting in the loss of the engine's service and excessive costs. With the changeable cooling air delivery system of the present invention, major engine disassembly is eliminated. An elongate member extends into a fluid control passage to establish a preselected flow area which can be changed. The time and expense required to change the cooling flow rate is drastically reduced because the elongate members are accessible external of the engine. The elongate member is removed from the engine and replaced by different elongate member having a different outer diameter of the stem or sleeve. The different diameter results in a new clearance or preselected flow area for cooling air to pass therethrough.

Abstract: A gas turbine engine having a turbine with internally cooled, stationary nozzles incorporated into first and second stage nozzle segments and a system for supplying air to the nozzles, for effecting a flow of cooling air into impingement and film cooling relationships with a tip shoe mounted in the nozzle case, and for generating a flow of air which first impingement cools a nozzle case lip supporting the upstream ends of the second stage nozzle segments and then acts as a buffer, keeping hot gases from entering the space between the nozzles and the nozzle case.

Abstract: A gas turbine engine having a turbine with internally cooled, stationary nozzles, a rotor with internally cooled blades, and systems for supplying air to the nozzles and rotor and for cooling the nozzle case.