-
公开(公告)号：US20160160670A1
公开(公告)日：2016-06-09
申请号：US14938484
申请日：2015-11-11
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala
CPC classification number: F01D9/041 , F01D5/02 , F01D5/143 , F01D15/12 , F01D25/24 , F05D2220/3212 , F05D2220/3215 , F05D2220/36 , F05D2240/12 , F05D2240/129 , F05D2240/80 , Y02T50/673
Abstract: A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance. The leading a trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length. A pitch-to-chord ratio of the pitch distance over the axial chord length is equal to or greater than 1.7.
Abstract translation: 可用于齿轮传动涡扇发动机的高压涡轮机的第一级叶片阵列包括沿其周向间隔开并且围绕发动机轴线定向的多个翼型件。 每个翼型件具有前缘和后缘，后缘由下一个相邻的后缘沿着圆周方向间隔开一个间距距离。 多个翼型中的每一个的后缘的前缘通过轴向弦长度轴向分开。 轴向弦长之间的俯仰距离的俯仰和弦比等于或大于1.7。
-
公开(公告)号：US20190153885A1
公开(公告)日：2019-05-23
申请号：US16195316
申请日：2018-11-19
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Russell J. Bergman
Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.
-
公开(公告)号：US20180258774A1
公开(公告)日：2018-09-13
申请号：US15918246
申请日：2018-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. Zelesky , Andrew S. Aggarwala
CPC classification number: F01D5/20 , F01D9/02 , F01D11/08 , F01D25/12 , F05D2220/32 , F05D2240/126 , F05D2240/55 , F05D2250/294 , Y02T50/673
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.
-
公开(公告)号：US09803559B2
公开(公告)日：2017-10-31
申请号：US14615665
申请日：2015-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew D. Burdick , Thomas J. Praisner , Andrew S. Aggarwala , Eric A. Hudson , Michael G. McCaffrey
CPC classification number: F02C9/20 , F01D5/148 , F01D9/02 , F01D11/025 , F01D17/162 , F02C3/04 , F05D2240/122 , Y02T50/672 , Y02T50/673 , Y10T137/0536
Abstract: One exemplary embodiment of this disclosure relates to a system including an airfoil having a static portion, a moveable portion, and a seal between the static portion and the moveable portion. The seal is moveable separate from the static portion and the moveable portion.
-
公开(公告)号：US20140090380A1
公开(公告)日：2014-04-03
申请号：US13663894
申请日：2012-10-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew S. Aggarwala , Eric A. Grover
CPC classification number: F01D5/143 , F04D29/321 , F04D29/681 , F05D2240/303 , F05D2240/80 , F05D2250/711 , F05D2250/712 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall near the leading edge of at least one of said plurality of airfoils, and a concave profiled region in the endwall near a middle of at least one of said plurality of flow passages.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括从所述多个翼型件中的至少一个翼型件的前缘附近的端壁延伸的凸形轮廓区域，以及在所述多个流动通道中的至少一个流动通道的中间附近的端壁中的凹形轮廓区域。
-
Patent Agency Ranking
公开(公告)号：US20160153304A1
公开(公告)日：2016-06-02
申请号：US14942484
申请日：2015-11-16
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Russell J. Bergman , Mark A. Boeke , Kyle C. Lana , Daniel A. Snyder
CPC classification number: F01D11/006 , F01D5/22 , F01D11/001 , F01D11/02
Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.
Abstract translation: 涡轮发动机的翼型段包括上游翼型组件，与上游翼型组件成旋转关系的下游翼型组件和集成在其间的边缘密封组件。 轮辋密封组件可以包括上游翼型组件的平台的倾斜下游部分，下游翼型组件的平台的上游部分和从上游部分径向向外突出的凸块。 下游部分和上游段彼此间隔开，在其间限定冷却空气的流动。 该部分和部分轴向重叠，使得该凸块与下游部分轴向对齐，以改善冷却效果并减少进入冷却腔的芯气流。
-
公开(公告)号：US20140154068A1
公开(公告)日：2014-06-05
申请号：US13664031
申请日：2012-10-30
Applicant: United Technologies Corporation
Inventor： Andrew S. Aggarwala , Timothy Charles Nash , Eunice Allen-Bradley , Eric A. Grover
CPC classification number: F01D9/02 , F01D5/143 , F01D5/145 , F04D29/324 , F04D29/542 , F04D29/681 , Y02T50/673
Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
Abstract translation: 公开了一种翼型阵列。 翼型阵列可以包括端壁和从端壁径向突出的多个翼型件。 每个翼型件可以具有在前缘和后缘之间以弦状轴向延伸的第一侧和相对的第二侧。 翼型件可以在端壁上周向间隔开，从而在相邻翼型之间限定多个流动通道。 翼型阵列还可以包括凸出的轮廓区域，该凸形轮廓区域从靠近所述多个翼型件中的至少一个的前缘的所述多个翼型件中的至少一个的第一侧面的端壁延伸，并且在所述多个翼型件中的凹形轮廓区域 并且延伸穿过所述多个流动通道中的所述至少一个。
-
公开(公告)号：US10815790B2
公开(公告)日：2020-10-27
申请号：US15918190
申请日：2018-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. Zelesky , Andrew S. Aggarwala
Abstract: An airfoil according to an example includes, among other things, a suction sidewall and a pressure sidewall. A tip wall extends from a leading edge to a trailing edge and joins respective outer ends of the suction and pressure sidewalls. A tip rib extends along a pressure side of the tip wall. A tip leakage control channel is provided at the tip wall and has a floor that extends between a first control channel vane sidewall and a second control channel vane sidewall established by a corresponding tip leakage control vane. Each of the tip leakage control vanes is contiguous with and extending from a suction side surface of the tip rib. The tip leakage channel extends toward the trailing edge while extending toward the suction sidewall. One or more of an internal cavity, a channel cooling aperture, and a sidewall microcircuit may be provided.
-
公开(公告)号：US10774659B2
公开(公告)日：2020-09-15
申请号：US15918246
申请日：2018-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. Zelesky , Andrew S. Aggarwala
Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall. The tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib. A tip leakage control channel at an outer surface of said tip wall, wherein said tip leakage control channel is between first and second tip leakage control vanes contiguous with a suction side surface of said tip rib, said tip leakage control channel extending toward said trailing edge while extending toward said suction sidewall. An air seal is radially outward of said tip wall and positioned to minimize leakage at said tip wall.
-
公开(公告)号：US20200024984A1
公开(公告)日：2020-01-23
申请号：US16225944
申请日：2018-12-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew S. Aggarwala , Timothy Charles Nash , Eunice Allen-Bradley , Eric A. Grover
Abstract: An airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
-
-
-
-
-
-
-
-
-
Search Results
19
records
(took 0.018 seconds)
