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公开(公告)号：US09702260B2
公开(公告)日：2017-07-11
申请号：US14882244
申请日：2015-10-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gary A. Schirtzinger , George J. Kramer
IPC: F16J15/447 , F01D11/00 , F01D11/08 , F16J15/3288
CPC classification number: F01D11/005 , F01D11/001 , F01D11/08 , F05D2220/32 , F05D2240/56 , F16J15/3288
Abstract: The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment.
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公开(公告)号：US09341377B2
公开(公告)日：2016-05-17
申请号：US13706404
申请日：2012-12-06
Applicant: United Technologies Corporation
Inventor： George J. Kramer
CPC classification number: F23R3/60 , F02K1/82 , F23R2900/00005 , F23R2900/00017 , Y10T29/4932
Abstract: A liner and attachment structure has an exhaust liner for use in a gas turbine engine. At least one hanger has feet secured to the liner. The hanger has an aperture extending at a central web. A flanged washer is received within the opening in the hanger. The flanged washer allows adjustment relative to the hanger. The flanged washer has a spherical recess. A collet has a plurality of part-spherical fingers separated by slots, and are received in the spherical recess of the flanged washer. A member extends into the collet to hold the part-spherical fingers radially outwardly. The member is also utilized to secure static structure, and to secure the liner to the static structure.
Abstract translation: 衬套和附接结构具有用于燃气涡轮发动机的排气衬套。 至少一个衣架有脚固定到衬垫上。 衣架具有在中央网处延伸的孔。 凸缘垫圈被接纳在衣架的开口内。 带法兰的垫圈允许相对于衣架进行调节。 凸缘垫圈有一个球形凹槽。 夹头具有多个由槽分开的部分球形指状物，并被容纳在带凸缘的垫圈的球形凹部中。 一个构件延伸到夹头中以将部分球形的手指径向向外保持。 该构件还用于固定静态结构，并将衬垫固定到静态结构。
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公开(公告)号：US20150369173A1
公开(公告)日：2015-12-24
申请号：US14761020
申请日：2014-02-11
Applicant: United Technologies Corporation
Inventor： Thomas M. Barry , George J. Kramer
CPC classification number: F02K1/822 , F02C3/04 , F02C3/14 , F02C7/14 , F02C7/18 , F02K1/80 , F05D2220/32 , F05D2250/28 , F05D2250/294 , F05D2250/324 , F05D2260/202 , F23R3/002 , Y02T50/675
Abstract: A liner portion has an exhaust liner portion with an inner face extending to an outward extending flange. Cooling grooves formed in the flange have a radially outward inlet point and a radially inner outlet point. A flow area at the inlet point is smaller than the flow area at the outlet point.
Abstract translation: 衬套部分具有排气衬套部分，其内表面延伸到向外延伸的凸缘。 形成在凸缘中的冷却槽具有径向向外的入口点和径向内部出口点。 入口点处的流动面积小于出口处的流动面积。
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公开(公告)号：US20150337732A1
公开(公告)日：2015-11-26
申请号：US14818392
申请日：2015-08-05
Applicant: United Technologies Corporation
Inventor： Robert Russell Mayer , George J. Kramer , Paul W. Palmer
Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.
Abstract translation: 燃气涡轮发动机包括与风扇流体连接的风扇和压缩机部。 压缩机包括高压压缩机和低压压缩机。 燃烧器流体地连接到压缩机部分。 涡轮部分流体地连接到燃烧器。 涡轮部分包括经由第一轴联接到高压压缩机的高压涡轮机。 低压涡轮机经由第二轴联接到低压压缩机。 齿轮架构在第二轴和风扇之间互连。 燃气涡轮发动机是具有大于六（6）的旁路比的高旁路齿轮飞机发动机。 低压涡轮机具有大于5的压力比，并且齿轮架构包括大于2.5:1的齿轮减速比。
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