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公开(公告)号：US20200149475A1
公开(公告)日：2020-05-14
申请号：US16595883
申请日：2019-10-08
Applicant: United Technologies Corporation
Inventor： Dale William Petty , Karl D. Blume , Joseph T. Caprario , Steven J. Bauer
Abstract: A disclosed gas turbine engine includes a compressor section, a combustor section, a first turbine section and a second turbine section. An outer case structure for the gas turbine engine includes a single-piece case structure with a turbine case portion and a transition case portion. The transition case portion is integrally formed with the turbine case portion as a single part module. A combustor case houses the combustor and an aft turbine case supports the low pressure turbine. The outer case includes a forward end attachable to the combustor case and an aft end attachable to the aft turbine.
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公开(公告)号：US10392966B2
公开(公告)日：2019-08-27
申请号：US15274306
申请日：2016-09-23
Applicant: United Technologies Corporation
Inventor： Joseph T. Caprario , Noah Wadsworth , Mark E. Marler , James P. Allore , Elizabeth F. Vinson
Abstract: A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.
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公开(公告)号：US20170328224A1
公开(公告)日：2017-11-16
申请号：US15154351
申请日：2016-05-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Joseph T. Caprario
CPC classification number: F01D5/3015 , F01D11/006 , F05D2220/32 , F05D2240/20 , F05D2260/30 , F05D2260/941 , F16B21/18
Abstract: A retaining ring assembly for a gas turbine engine may include a first engine component and a second engine component. A retaining ring may be disposed between the first engine component and the second engine component. The retaining ring may be circumferentially discontinuous and may include a first terminal portion having at least one of a tapered or a contoured geometry. A thickness of the retaining ring at the first terminal portion may be less than a thickness of the retaining ring away from the first terminal portion.
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公开(公告)号：US20150345337A1
公开(公告)日：2015-12-03
申请号：US14759769
申请日：2013-01-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Dale William Petty , James P. Allore , Joseph T. Caprario , Steven J. Bauer
CPC classification number: F01D25/28 , F01D25/162 , F01D25/24 , F05D2230/64 , Y10T29/49828
Abstract: A turbine housing section includes a radially inner case centered on a first axis, and a radially outer case spaced radially outwardly of the inner case, and centered on a second axis. The first and second axes are offset relative to each other. A plurality of tie rods include a threaded nut received on a tie rod, with the plurality of tie rods connecting the inner and outer cases. The plurality of tie rods are spaced circumferentially about both of the first and second axes, and extend for distinct lengths between the inner and outer cases such that the inner and outer cases are held at a position wherein the first and second axes are offset
Abstract translation: 涡轮机壳体部分包括以第一轴线为中心的径向内部壳体，以及径向外部壳体，其位于内部壳体的径向外侧并且以第二轴线为中心。 第一和第二轴相对于彼此偏移。 多个拉杆包括容纳在拉杆上的螺纹螺母，多个拉杆连接内壳和外壳。 多个拉杆围绕第一和第二轴线周向间隔开，并且在内壳体和外壳体之间延伸不同长度，使得内壳体和外壳体保持在第一和第二轴线偏移的位置
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