AXIAL FLOW GAS TURBINE ENGINE
    2.
    发明专利

    公开(公告)号:JP2000186507A

    公开(公告)日:2000-07-04

    申请号:JP35530799

    申请日:1999-12-15

    Abstract: PROBLEM TO BE SOLVED: To provide an axial flow gas turbine engine which can minimize a gas dynamical clearance under cruising condition of the engine, which can be assembled, and in which a low pressure compressor and a low pressure turbine assembly can be inspected. SOLUTION: A rotary machine which has rotor raw material 54-56, 114 and seal lands 86, 112 has been disclosed. Details of various structures are developed for easy assembly of machine. In one embodiment, clearance is established between a moving blade 66 and a seal land 86 to make assembly of components possible, and a certain clearance which is acceptable under steady state of an engine is supplied.

    ROTARY MACHINE ASSEMBLING METHOD AND GAS TURBINE ENGINE ASSEMBLING METHOD

    公开(公告)号:JP2000186571A

    公开(公告)日:2000-07-04

    申请号:JP35530899

    申请日:1999-12-15

    Abstract: PROBLEM TO BE SOLVED: To minimize gas dynamic clearance in the cruise operating state of an engine by supplying a lubricant to the surface of a seal land. SOLUTION: A rotary machine assembling method has a step of forming a sub-assembly including a lower pressure compressor rotary assembly and a step of forming a case assembly for a low pressure rotary assembly. Further, the method has a step of supplying a lubricant to at least one seal land 112 before the case assembly is assembled in the rotary assembly. The clearance can be made in the minimum clearance dimensions by using silicone oil as a lubricant, and a pilot rod of a blade which is normally difficult to be turned by hand can be freely turned by supplying silicone foil to the seal land. Lowering of characteristic of a component where the lubricant touches is prevented.

    7.
    发明专利
    未知

    公开(公告)号:DE69926594D1

    公开(公告)日:2005-09-15

    申请号:DE69926594

    申请日:1999-12-22

    Abstract: A gas turbine engine comprises a rotor (50) provided with rotor blades (50,56,58,62,64,66), and a stator (68) provided with stator varies (92,94,96,98,102,104). Airseals are formed between the rotor (56) and stator (68) by providing rubstrips (86) adjacent the tips of the rotor blades (54-66), and by providing seals knife edge seals (112,114) adjacent the tips of the stator varies (92-104). In order to minimise the clearance between the rotor and stator during operation, and hence improve the efficiency of the engine, during construction an interference fit is provided between the rotor (50) and stator (68) say between the rotor blades (54-66) and the rubstrips (86), so that during operation the clearance between the rotor (50) and the stator (68) is minimised and the engines efficiency is improved.

    10.
    发明专利
    未知

    公开(公告)号:DE69926594T2

    公开(公告)日:2006-05-18

    申请号:DE69926594

    申请日:1999-12-22

    Abstract: A gas turbine engine comprises a rotor (50) provided with rotor blades (50,56,58,62,64,66), and a stator (68) provided with stator varies (92,94,96,98,102,104). Airseals are formed between the rotor (56) and stator (68) by providing rubstrips (86) adjacent the tips of the rotor blades (54-66), and by providing seals knife edge seals (112,114) adjacent the tips of the stator varies (92-104). In order to minimise the clearance between the rotor and stator during operation, and hence improve the efficiency of the engine, during construction an interference fit is provided between the rotor (50) and stator (68) say between the rotor blades (54-66) and the rubstrips (86), so that during operation the clearance between the rotor (50) and the stator (68) is minimised and the engines efficiency is improved.

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