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A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposit

A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides.

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A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposit

A butterfly valve for a gas turbine engine includes a valve shaft and a valve disk. The valve disk has a centerline axis that extends through the valve disk. The valve disk also includes a shaft opening, an outer periphery, an outer surface, a first side, and a second side. The first side is opposite the second side. The shaft opening extends through the valve disk adjacent the centerline axis, and is sized to receive the valve shaft therein. The disk outer surface extends over the first and second sides, and is tapered between the outer periphery and the centerline axis over at least one of the disk first and second sides. aim 1, wherein the air-fuel mixture generating section includes;a throat portion connecting to the air inlet and having a circular cross-section of diminishing diameter; anda fuel passage connecting to the fuel inlet and merging with throat nozzles formed in the throat portion to communicate with the air-fuel mixture generating passage.3. A gas-turbine engine combustor according to claim 2, wherein, defining a radius from a center of the throat portion to a wall surface as r, each of the throat jets is formed so as to inject the gaseous fuel from a point on a line offset n times the radius r from an arbitrary line passing through the center of the throat portion.4. A gas-turbine engine combustor according to claim 3, wherein n is 0.7 to 0.9.5. A gas-turbine engine combustor according to claim 1, wherein the air-fuel mixture generating passage is provided with the throttle section of diminishing diameter at a location close to the nozzle opened into the combustion chamber at the end of the air-fuel mixture generating passage.6. A gas-turbine engine according to claim 1, wherein the output shaft of the turbine is connected to an electric generator.