Honda Motor Co., Ltd.

Honda Giken Kogyo Kabushiki Kaisha

Masayuki Fukutani

Etsuo Noda

Mineyasu Oana

Osamu Kawamoto

Kenichi Senda

Atsukuni Waragai

Hiroki Nagata

In a part-fastening structure, one of respective threads of a first nut member for fastening a first part and a second nut member for fastening a second part, is a right-hand thread, and the other is a left-hand thread. The members are connected together by a connecting member against relative rotation. Thus, rotation of the first member in its loosening direction acts in a direction of fastening the second member via the connecting member, and rotation of the second member in its loosening direction acts in a direction of fastening the first member via the connecting member, so that looseness of both the members is prevented, while reducing the number of locking parts to minimize an increase in an axial dimension.

Part-fastening structure

To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. The intake passageincludes an inlet portion, a curved portionand a reduced diameter portion. The bypass ductis curved away from the central axial line CL in a region corresponding to the curved portionand reduced diameter portionof the intake passage. Between the intake passageand bypass ductis defined an annular space. In the reduced diameter portion, the outer lineris formed with a large number of foreign matter introduction openingsin a circumferential arrangement for communication between the intake passageand annular space. The inner casingis formed with a plurality of foreign matter ejection holesin a circumferential arrangement in a part thereof that curves outward for communication between the annular spaceand bypass duct

Gas turbine engine provided with a foreign matter removal passage

In a device for supplying secondary air in a gas turbine engine provided with an inner shaft () and a hollow outer shaft () coaxially nested with each other, a seal air introduction passage () is defined inside the engine for introducing a part of high pressure air drawn from a high pressure compressor into a seal section provided in each of the bearing boxes for supporting the inner and outer shafts; and a swirl air cooling turbine () is provided in the seal air introduction passage and attached to a part attached to the outer shaft in a rotationally fast manner. The swirl air cooling turbine () is formed around a section of the outer shaft intermediate between the high pressure compressor and the high pressure turbine, the swirl air cooling turbine including a spiral flow path extending in a substantially cylindrical plane coaxial with the outer shaft. Because the high pressure swirl air is cooled by the swirl air cooling turbine provided in a radially central part, the energy of the swirl air is effectively expended, and this prevents the generation of a stagnation zone. Thereby, the secondary air can be favorably cooled before it is forwarded to the user such as the bearing boxes without causing an undue rise in the pressure of the impeller back chamber.

Device for supplying secondary air in a gas turbine engine

In a device for supplying secondary air in a gas turbine engine provided with an inner shaft () supporting a low pressure compressor and a low pressure turbine and a hollow outer shaft () coaxially nested with the inner shaft and supporting a high pressure compressor and a high pressure turbine, a seal air introduction passage () for introducing a part of high pressure air drawn from the high pressure compressor into a seal section provided in each of the bearing boxes is provided with a high pressure air introduction turbine () attached to the outer shaft in a rotationally fast manner. Owing to the use of the high pressure air introduction turbine, work is extracted from the seal air and cooling air derived from the supplied air and having a high temperature and high pressure air so that an excessive rise in the seal pressure at the normal rotational speed can be avoided and, at the same time, the supplied air can be reduced in temperature thereby avoiding an excessive rise in the temperature of the lubricating oil for the bearing.

Provided is a device for supplying seal air to the bearings of a gas turbine engine which allows the seal pressure to be kept even between the front and rear gear boxes without complicating the passages for supplying the seal air to the bearing boxes. Sealing air drawn from a part of high pressure compressor is conducted through passages defined between the inner periphery of the rotors of the high pressure compressor and a high pressure turbine and the outer periphery of the outer shaft, and is distributed to the front and rear bearing boxes. By appropriately providing narrowed parts in these passages, seal air is evenly distributed between the front and rear bearing boxes. Thus, even in case of a failure of one of the oil seals, any concentrated leakage of the lubricating oil can be avoided.

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Wako, Japan

Masayuki Fukutani