-
公开(公告)号：US09945295B2
公开(公告)日：2018-04-17
申请号：US14727475
申请日：2015-06-01
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Donald W. Peters , James P. Bangerter
CPC classification number: F02C7/28 , F02C3/04 , F02K1/805 , F05D2220/32 , F05D2240/55 , F05D2240/58 , F05D2250/14 , F05D2250/314 , F05D2250/34 , F05D2250/41 , F05D2260/38 , F05D2260/57 , F05D2300/603 , F05D2300/6034 , F16J15/3488 , Y02T50/672
Abstract: A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.
-
公开(公告)号：US20180080335A1
公开(公告)日：2018-03-22
申请号：US15826860
申请日：2017-11-30
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , John T. Ols
CPC classification number: F01D11/005 , F01D9/02 , F01D9/041 , F01D9/06 , F01D25/26 , F02C3/04 , F02C7/28 , F05D2220/32 , F05D2240/128 , F05D2240/58 , F05D2240/80
Abstract: A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.
-
公开(公告)号：US09869204B2
公开(公告)日：2018-01-16
申请号：US14640323
申请日：2015-03-06
Applicant: United Technologies Corporation
Inventor： Joshua Daniel Winn , Anthony P. Cherolis , Steven D. Porter , Christopher Treat , Kevin Zacchera
CPC classification number: F01D25/145 , F01D9/065 , F01D25/12 , F01D25/162 , F01D25/24 , F01D25/243 , F01D25/28 , F05D2260/20 , Y02T50/672 , Y02T50/676
Abstract: A mid-turbine frame for a gas turbine engine according to an example of the present disclosure includes, among other things, a first frame case, a flange coupled to the first frame case, and a heat shield adjacent to the flange and between adjacent spokes. A method of cooling a portion of a gas turbine engine is also disclosed.
-
公开(公告)号：US09850771B2
公开(公告)日：2017-12-26
申请号：US14603414
申请日：2015-01-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven D. Porter , John T. Ols
CPC classification number: F01D11/005 , F01D9/02 , F01D9/041 , F01D9/06 , F01D25/26 , F02C3/04 , F02C7/28 , F05D2220/32 , F05D2240/128 , F05D2240/58 , F05D2240/80
Abstract: A sealing arrangement for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a groove that extends between an upstream rail and a downstream rail, a complementary static structure spaced from the groove, and a seal positioned within the groove and configured to seal a clearance between at least one of the upstream rail and the downstream rail and the complementary static structure.
-
公开(公告)号：US09828881B2
公开(公告)日：2017-11-28
申请号：US14662347
申请日：2015-03-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Seth A. Max , Anthony P. Cherolis , Steven D. Porter , Joshua D. Winn , Gregory E. Reinhardt , Jeffrey J. Lienau
CPC classification number: F01D25/28 , F01D11/003 , F01D11/006 , F01D25/24 , F01D25/243 , F05D2220/32 , F05D2230/00 , F05D2230/60 , F05D2240/55 , F05D2240/60 , F05D2260/97
Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.
-
Patent Agency Ranking
公开(公告)号：US20170328204A1
公开(公告)日：2017-11-16
申请号：US15155242
申请日：2016-05-16
Applicant: United Technologies Corporation
Inventor： Thomas A. Mariano , Steven D. Porter
Abstract: Methods of manufacturing toothed components for gas turbine engines are provided. The methods include forming a first tooth in the component with a top land, a bottom land, a side wall extending therebetween, and a fillet radius transitioning between the side wall and the bottom land, forming a second tooth in the component adjacent the first tooth, the second tooth having a top land, a bottom land, a side wall extending therebetween and facing the first tooth, and a fillet radius transitioning between the side wall and the bottom land, the bottom land of the second tooth extending toward the bottom land of the first tooth, wherein the bottom lands define a gable area of the component, and forming a stress relief feature in the gable area such that the stress relief feature reduces a stress concentration near the gable area during operation of the toothed component.
-
公开(公告)号：US20170268354A1
公开(公告)日：2017-09-21
申请号：US15070789
申请日：2016-03-15
Applicant: United Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
CPC classification number: F01D9/02 , F01D5/066 , F01D5/3015 , F01D25/246 , F02C3/04 , F05D2220/32 , F05D2260/30
Abstract: According to one or more embodiments, a cover plate for a gas turbine engine is provided. The cover plate includes a cover plate body that extends from a disc blade attachment radially along an outside surface of a disc web to a disc bore of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion extending from the inner most end of the cover plate body toward the disc bore, and wherein the attachment protrusion is configured to engage with a retention ring.
-
公开(公告)号：US20160208655A1
公开(公告)日：2016-07-21
申请号：US14598574
申请日：2015-01-16
Applicant: United Technologies Corporation
Inventor： Jorge I. Farah , Steven D. Porter , Paul K. Sanchez , Joseph J. Sedor
IPC: F01D25/28
CPC classification number: F01D25/28 , F01D9/065 , F01D25/162 , F02C7/20 , F05D2220/32 , F05D2230/60 , F05D2260/31
Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case that includes a bolt opening and at least one spoke for connecting an outer frame case to the inner frame case that includes an inlet passage that extends in a radial direction. A central bolt extends through the bolt opening for securing at least one spoke to the inner frame case.
Abstract translation: 用于燃气涡轮发动机的中涡轮机框架包括内框架壳体，其包括螺栓开口和用于将外框架壳体连接到内框架的至少一个辐条，所述内框架壳体包括沿径向方向延伸的入口通道。 中心螺栓延伸穿过螺栓开口，用于将至少一个辐条固定到内框架壳体上。
-
99.发明申请公开(公告)号：US20160177755A1
公开(公告)日：2016-06-23
申请号：US14862351
申请日：2015-09-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven D. Porter , John T. Ols , Kyle C. Lana
CPC classification number: F01D9/02 , F01D1/04 , F01D5/081 , F01D11/001 , F05D2240/80 , Y02T50/676
Abstract: A gas-turbine engine is provided. The gas-turbine engine comprises a high pressure turbine with an aft blade platform. A static structure may be disposed aft of the high pressure turbine and proximate a cavity defined by the aft blade platform. A vane of the static structure may have a vane platform with a shaped tip extending into the cavity.
Abstract translation: 提供燃气涡轮发动机。 燃气涡轮发动机包括具有后叶片平台的高压涡轮机。 静态结构可以设置在高压涡轮机的后方并且靠近由后叶片平台限定的空腔。 静态结构的叶片可以具有叶片平台，其具有延伸到空腔中的成形尖端。
-
100.发明申请公开(公告)号：US20160153296A1
公开(公告)日：2016-06-02
申请号：US14900737
申请日：2014-06-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John T. Ols , Richard N Allen , Paul K. Sanchez , Steven D. Porter , Jonathan Lemoine
CPC classification number: F01D9/041 , F01D5/082 , F01D11/003 , F01D11/02 , F05D2240/12 , F05D2240/80
Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.
Abstract translation: 燃气涡轮发动机内的界面包括由叶片平台的一部分限定的密封表面。 密封件与所述密封表面接触。 屏障横向于密封表面。
-
-
-
-
-
-
-
-
-
Search Results
100
records
(took 0.021 seconds)
