Abstract: To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract: A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (RH/RL) of a pressure ratio (RH) of the high-pressure compressor to a pressure ratio (RL) of the low-pressure compressor is within a range of 4.5 to 6.0.

Abstract: [Object] To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. [Means] The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

Abstract: A compressor having a front fan, which rotates to compress intake air, a single-stage low-pressure compressor which is disposed behind the front fan to compress intake air, and a single-stage high-pressure compressor which compresses the compressed air compressed by the low-pressure compressor; a ratio (RH/RL) of a pressure ratio (RH) of the high-pressure compressor to a pressure ratio (RL) of the low-pressure compressor is within a range of 4.5 to 6.0.

Abstract: In an impeller for centrifugal compressors comprising a plurality of blades each having a base end attached to a central hub, each of the blades is given with a thickness which increases progressively toward a hub end thereof, and a suction surface side of the blade is given with a greater thickness increase rate with respect to a neutral plane than a pressure surface side of the blade. Thereby, the inter-blade channel is narrowed locally in the region near the hub end of the suction surface of each blade, and this locally reduces the aerodynamic loading on the blade. In particular, the surge property is improved, and the generation of radially outwardly directed secondary flows can be minimized. This allows the distribution of aerodynamic loading in the radial direction or from the tip end to the hub end of each blade to be controlled at will, and enables the optimum design of the impeller.

Abstract: A chemically resistant, extractable free, composite laminar film including polyimide, PFA and m-PTFE layers.

Abstract: In an impeller for centrifugal compressors comprising a plurality of blades each having a base end attached to a central hub, each of the blades is given with a thickness which increases progressively toward a hub end thereof, and a suction surface side of the blade is given with a greater thickness increase rate with respect to a neutral plane than a pressure surface side of the blade. Thereby, the inter-blade channel is narrowed locally in the region near the hub end of the suction surface of each blade, and this locally reduces the aerodynamic loading on the blade. In particular, the surge property is improved, and the generation of radially outwardly directed secondary flows can be minimized. This allows the distribution of aerodynamic loading in the radial direction or from the tip end to the hub end of each blade to be controlled at will, and enables the optimum design of the impeller.

Abstract: A sewing machine with an upper feed mechanism includes: a sewing machine head; a needle plate; first, second and third shafts each extending from the sewing machine head vertically downwardly toward the needle plate, each shaft having a lower end; a needle secured to the lower end of the first shaft; a feed element having one end carried by the lower end of the second shaft and the other end located forwardly of the path of the needle; an upper feed dog formed in the other end of the feed element and confronting the needle plate; and a presser foot mounted to the lower end of the third shaft, wherein the first, second and third shafts being moved in timed relation to one another so as to allow a workpiece to be sandwiched between the presser foot and the needle plate, and the upper feed dog cooperating with a lower feed dog located below the needle plate to clamp and feed the workpiece to the path of the needle whereby stitches are formed, and wherein the first, second and third shafts are juxtaposed in that