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公开(公告)号：US20180106194A1
公开(公告)日：2018-04-19
申请号：US15784629
申请日：2017-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Merry , Gabriel L. Suciu , James W. Norris
CPC classification number: F02C3/073 , F02K1/04 , F02K3/068 , F05D2300/603 , F05D2300/614 , Y02T50/672 , Y10T29/49346
Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
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公开(公告)号：US20150308342A1
公开(公告)日：2015-10-29
申请号：US14524736
申请日：2014-10-27
Applicant: United Technologies Corporation
Inventor： James W. Norris
CPC classification number: F02C7/16 , F01D5/045 , F01D5/046 , F01D5/088 , F01D5/181 , F04D29/285 , F04D29/584 , F05D2260/207 , F05D2260/208 , F05D2260/2322
Abstract: A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
Abstract translation: 燃气涡轮发动机径向叶轮包括沿着径向叶轮的中性弯曲平面彼此固定的第一和第二叶轮部分。 蒸气冷却腔设置在第一和第二叶轮部分之间。 中性弯曲平面布置在蒸气冷却腔中。
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Patent Agency Ranking
公开(公告)号：US08967945B2
公开(公告)日：2015-03-03
申请号：US14138889
申请日：2013-12-23
Applicant: United Technologies Corporation
Inventor： Craig A. Nordeen , James W. Norris
CPC classification number: F01D17/16 , F01D17/162 , F02C9/20 , F02K3/06 , F05D2220/327 , Y10S415/914
Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.
Abstract translation: 根据本发明的顶端涡轮发动机包括用于风扇和/或压缩机的多个可独立变化的入口导叶。 致动器可操作地联接到每个翼片，使得每个致动器可以选择性地改变其相关联的入口引导叶片的翼片。 在一个实施例中，入口导向叶片各自包括可枢转地安装的翼片，其可独立于至少一些其它入口导向叶片的翼片而变化。 在另一个实施例中，入口导向叶片各自包括至少一个流体出口或喷嘴，其引导加压空气，由相关联的致动器控制，以控制入口失真。
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公开(公告)号：US10760423B2
公开(公告)日：2020-09-01
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, Jr. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
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公开(公告)号：US10760483B2
公开(公告)日：2020-09-01
申请号：US15784629
申请日：2017-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brian Merry , Gabriel L. Suciu , James W. Norris
Abstract: A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.
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公开(公告)号：US20180223668A1
公开(公告)日：2018-08-09
申请号：US15947119
申请日：2018-04-06
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve, JR. , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk at an interface, where the interface is defined along a spoke. A spool for a gas turbine engine includes the rotor disk, the plurality of blades with the interface defined along the spoke radially inboard of a blade platform, a rotor ring axially adjacent to the rotor disk, and a plurality of core gas path seals which extend from the rotor ring. Each of the plurality of core gas path seals extends from the rotor ring at a seal interface, with the seal interface defined along a spoke and the plurality of core gas path seals being axially adjacent to the blade platform.
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公开(公告)号：US09790859B2
公开(公告)日：2017-10-17
申请号：US14524736
申请日：2014-10-27
Applicant: United Technologies Corporation
Inventor： James W. Norris
CPC classification number: F02C7/16 , F01D5/045 , F01D5/046 , F01D5/088 , F01D5/181 , F04D29/285 , F04D29/584 , F05D2260/207 , F05D2260/208 , F05D2260/2322
Abstract: A gas turbine engine radial impeller includes first and second impeller portions that are secured to one another along a neutral bending plane of the radial impeller. A vapor cooling cavity is provided between the first and second impeller portions. The neutral bending plane is arranged in the vapor cooling cavity.
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