Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A compressor bleed valve system for bleeding air from a gas turbine engine compressor comprises a bladder inflatable between at least a collapsed position and an expanded position for selectively opening and closing a compressor airbleed passage.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A casing for a gas turbine includes a fan case, an intermediate case and a gas generator case integrated with one another.

Abstract: A compressor bleed valve system for bleeding air from a gas turbine engine compressor comprises a bladder inflatable between at least a collapsed position and an expanded position for selectively opening and closing a compressor airbleed passage.

Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.

Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A method of manufacturing a seamless self-supporting metal part using nickel vapor deposition, where the part has a selected minimum thickness, a first aerodynamically contoured surface and a second substantially parallel surface. The method replaces labor intensive welding of individually manufactured sheet metal segments for complex aerodynamic shapes, and produces a part with higher accuracy, less cost, controlled strength and hardness properties. Nickel vapor deposition is commonly used for plating electronic components, and for producing a metallic lining for plastic injection moulds. The seamless sheet metal part is cast by: fabricating a mould with at least one mould surface being a negative of the first surface of the part; enclosing the mould in a nickel vapor deposition chamber; depositing nickel on the mould surface by nickel vapor deposition until a blank of nickel is deposited having at least the minimum thickness and an external deposition surface; and separating the blank from the mould.

Abstract: The invention provides a diffuser assembly constructed of internal and external concentrically nested bowl-shaped shells for directing an outward flow of compressed air from a centrifugal compressor impeller to an axially rearward diffused annular flow. The shells can be easily manufactured from nested metal castings thereby eliminating much of the cost and time involved in fabricating prior art diffusers of multiple formed tubes brazed to a separately machined hub. The novel diffuser assembly has two concentrically nested bowl-shaped shells, each shell having an inner peripheral compressor impeller casing about a central opening, and an outer edge. Opposing nested surfaces of the shells have an array of mating grooves separated by abutting seam edges thus defining individual diffuser ducts extending from the compressor impeller casings to the outer shell edges when the shells are secured together.