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公开(公告)号：CA1129776A
公开(公告)日：1982-08-17
申请号：CA346415
申请日：1980-02-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONSARRAT WILLIAM G
Abstract: FULL HOOP BLEED MANIFOLDS FOR LONGITUDINALLY SPLIT COMPRESSOR CASES A compressor case structure capable of enhanced active clearance control within the structure is disclosed. Various construction details which enable the discharge of cooling air against the case and which minimize thermal distortion of the case are developed. The concepts are applied to a longitudinally split compressor case and include an external bleed manifold of circular cross section which extends across the longitudinal split in the case. Cooling air is dischargeable beneath the manifold to cool the case structure. EH-6396
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公开(公告)号：US3907455A
公开(公告)日：1975-09-23
申请号：US44040774
申请日：1974-02-07
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONSARRAT WILLIAM G
CPC classification number: F04D29/403
Abstract: In a multistage split compressor wherein the low pressure compressor has a plurality of stages on one rotor and the high pressure compressor has a plurality of stages on another rotor, the low pressure compressor is removable as a unit from the high pressure compressor by making the intermediate case in two pieces, one integral with the low pressure compressor case with an associated bearing for the low pressure rotor and the other integral with the high pressure compressor case also with an associated bearing for the high pressure rotor. By having these two pieces removably secured together, the associated compressor cases may be separated by removal of the attachment devices holding the cases together, and each case carries with it the associated bearing for the enclosed rotor.
Abstract translation: 在多级压缩机中，低压压缩机在一个转子上具有多个级，而高压压缩机在另一个转子上具有多个级，低压压缩机可作为一个单元从高压压缩机中取出， 壳体分为两个部分，一个与低压压缩机壳体一体，其具有用于低压转子的相关轴承，另一个与高压压缩机壳体集成，还具有用于高压转子的相关联的轴承。 通过将这两个部件可拆卸地固定在一起，相关的压缩机壳体可以通过移除将壳体保持在一起的附接装置而分开，并且每个壳体都带有用于封闭转子的相关轴承。
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Patent Agency Ranking
公开(公告)号：FR2631385A1
公开(公告)日：1989-11-17
申请号：FR8906303
申请日：1989-05-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DENNISON WILLIAM T , BRODELL ROBERT F , MONSARRAT WILLIAM G
IPC: F02C7/20
Abstract: A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.
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公开(公告)号：GB2219046A
公开(公告)日：1989-11-29
申请号：GB8909977
申请日：1989-05-02
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DENNISON WILLIAM T , BRODELL ROBERT F , MONSARRAT WILLIAM G
IPC: F02C7/20
Abstract: A gas turbine fan engine with improved maintainability features is disclosed. Forward and rearward sections of the core of the engine are joined one to the other, and each are independently separable from the pylon on which the engine is mounted without the necessity of removing the other from the airplane.
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公开(公告)号：CA1128422A
公开(公告)日：1982-07-27
申请号：CA346418
申请日：1980-02-26
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONSARRAT WILLIAM G , NEAL WILLIAM F
Abstract: COMPRESSOR STRUCTURE ADAPTED FOR ACTIVE CLEARANCE CONTROL A compressor structure for a gas turbine engine capable of enhanced active clearance control within the compressor is disclosed. Various construction details which enable the discharge of cooling air against the compressor case and which minimize thermal distortion of the case are developed. The concepts are applied to a longitudinally split compressor case and include an external bleed manifold of circular cross section which extends across the longitudinal split in the case. Cooling air is dischargeable beneath the manifold to cool the case structure. Heat shields are provided in access ports to the manifold to inhibit heat transfer to the compressor case at the local regions of the ports. EH-6395
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公开(公告)号：CA1164348A
公开(公告)日：1984-03-27
申请号：CA376315
申请日：1981-04-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MONSARRAT WILLIAM G
Abstract: Flow Directing Assembly For A Gas Turbine Engine A nonrotating flow directing assembly 14 for a gas turbine engine is disclosed. The flow directing assembly is formed of a circumferentially segmented inner case 24 supported by an annular sleeve 22. The inner case 24 is formed of a plurality of arcuate segments 26 extending axially continuously through the engine. A method of assembling the circumferentially continuous annular sleeve about an axially continuous rotor is also disclosed. In an alternate embodiment the inner case 124 is formed of several pluralities of arcuate segments 126.
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公开(公告)号：CA1162148A
公开(公告)日：1984-02-14
申请号：CA376278
申请日：1981-04-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BRODELL ROBERT F , COMEAU ROGER J , MONSARRAT WILLIAM G
Abstract: A non-rotating flow directing assembly for a gas turbine engine is disclosed. The flow directing assembly is formed of a circumferentially segmented inner case supported by an annular sleeve. The inner case is formed of a plurality of arcuate segments extending axially continuously through the engine. A method of assembling the circumferentially continuous annular sleeve about an axially continuous rotor is also disclosed. In an alternate embodiment the inner case is formed of several pluralities of arcuate segments.
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