公开(公告)号：US10385728B2

公开(公告)日：2019-08-20

申请号：US15034951

申请日：2014-11-03

Applicant: United Technologies Corporation

Inventor： Thomas N. Slavens ,  Eric A. Grover ,  John D. Teixeira

IPC: F01D25/12 ,  F01D17/16 ,  F01D5/14 ,  F01D9/04 ,  F01D9/06 ,  F01D5/02 ,  F01D5/12 ,  F01D17/14 ,  F02C3/04

Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

公开(公告)号：US09951638B2

公开(公告)日：2018-04-24

申请号：US14859845

申请日：2015-09-21

Applicant: United Technologies Corporation

Inventor： Eric A. Grover

IPC: F01D11/00 ,  F01D5/02 ,  F01D9/04

CPC classification number: F01D11/001 ,  F01D5/02 ,  F01D9/041 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2240/55

Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.

公开(公告)号：US09926806B2

公开(公告)日：2018-03-27

申请号：US14598822

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Thomas J. Praisner ,  Eric A. Grover ,  Renee J. Jurek

IPC: F01D5/14 ,  F01D25/06 ,  F01D9/04 ,  F01D5/12 ,  F01D25/24 ,  F04D29/52 ,  F04D29/68 ,  F04D29/54 ,  F04D27/02

CPC classification number: F01D25/06 ,  F01D5/12 ,  F01D5/143 ,  F01D5/145 ,  F01D9/041 ,  F01D25/24 ,  F04D27/02 ,  F04D27/0207 ,  F04D29/526 ,  F04D29/547 ,  F04D29/685 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/24 ,  F05D2250/70 ,  F05D2260/941 ,  F05D2260/96 ,  Y02T50/673

Abstract: A turbomachine includes an annular flow path section between a plurality of radially extending stator vanes and a plurality of radially extending rotor blades. At least a first portion of the flow path section has a circumferentially varying outer periphery which includes a recess circumferentially alternating with axisymmetric surfaces.

公开(公告)号：US20170335712A1

公开(公告)日：2017-11-23

申请号：US15161436

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Pitchaiah Vijay Chakka ,  Eric A. Grover ,  John D. Teixeira

IPC: F01D17/16 ,  F01D9/04

CPC classification number: F01D17/162 ,  F01D9/041 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2250/35 ,  F05D2250/90 ,  Y02T50/673

Abstract: Airfoils are provided having a body having a leading edge, a trailing edge, a first end surface, and a second end surface opposite the first end surface, wherein (i) a first true chord length is a line extending from a first leading edge point to a first trailing edge point and (ii) a second true chord length is a line extending from a second leading edge point to a second trailing edge point, a first button located on the first end surface of the airfoil body, the first button having a first diameter and a first attachment device extending from the first button to enable rotation of the airfoil body about an attachment device axis. The first diameter is at least 15% of the first true chord length or the attachment device axis is located 10% of the first true chord length from the leading edge point.

公开(公告)号：US20160237845A1

公开(公告)日：2016-08-18

申请号：US15027526

申请日：2014-10-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John D. Teixeira ,  Eric A. Grover ,  Raymond Surace

IPC: F01D17/16

CPC classification number: F01D17/162 ,  F01D5/143 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.

Abstract translation: 燃气涡轮发动机部件包括外径端壁，位于外径端壁的径向内侧的内径端壁，以及支撑在外端壁与内端壁之间的至少一个主体，用于绕轴线转动。 主体包括通过第一间隙与外径端壁隔开的外径表面，以及通过第二间隙与内径端壁隔开的内径表面。 外径和内径表面以及外径和内径端壁构造成使得当主体围绕轴线旋转时，第一和第二间隙的尺寸基本保持不变。

公开(公告)号：US09212558B2

公开(公告)日：2015-12-15

申请号：US13663977

申请日：2012-10-30

Applicant: United Technologies Corporation

Inventor： Thomas J. Praisner ,  Andrew S. Aggarwala ,  Eric A. Grover ,  Renee J. Jurek

IPC: F01D9/00 ,  F02C3/04 ,  F01D5/14

CPC classification number: F01D5/145 ,  F01D5/143 ,  F04D29/324 ,  F04D29/329 ,  F04D29/547 ,  F04D29/681 ,  F05D2240/123 ,  F05D2240/305 ,  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 airfoil array may further include a convex profiled region extending from the endwall adjacent the first side of at least one of said plurality of airfoils and near the leading edge of the at least one of said plurality of airfoils. The airfoil array may further include a concave profiled region in the endwall adjacent the first side of said at least one of said plurality of airfoils and aft of the convex profiled region.

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。 翼型阵列还可以包括从邻近所述多个翼型中的至少一个翼型件的第一侧的端壁延伸并且在所述多个翼型中的至少一个翼型件的前缘附近的凸形轮廓区域。 所述翼型阵列还可包括邻近所述多个翼型件中的所述至少一个翼型件的第一侧和所述凸形轮廓区域的后部的所述端壁中的凹形轮廓区域。

公开(公告)号：US11473434B2

公开(公告)日：2022-10-18

申请号：US16654380

申请日：2019-10-16

Applicant: United Technologies Corporation

Inventor： Timothy Charles Nash ,  Gary A. Zess ,  Eric A. Grover ,  Jin Hu

IPC: F01D5/14 ,  F01D9/02

Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

公开(公告)号：US11028717B2

公开(公告)日：2021-06-08

申请号：US15632628

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Armando Amador ,  Nasr A. Shuaib ,  Martin J. Walsh ,  William G. Sheridan ,  Eric A. Grover

IPC: F01D11/04 ,  F01D25/18 ,  F16C33/66 ,  F01D25/16 ,  F16C33/76 ,  F01D5/02 ,  F02K3/06 ,  F04D25/04

Abstract: A bearing assembly according to an example of the present disclosure includes, among other things, a bearing situated in a bearing compartment, a seal assembly that defines the bearing compartment, at least one deflector between the bearing and the seal assembly that is rotatable about an axis, and a coalescer at least partially extending about the at least one deflector to define a fluid passage. A method of sealing is also disclosed.

公开(公告)号：US10975713B2

公开(公告)日：2021-04-13

申请号：US16239616

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： Eric A. Grover ,  Brian F. Hilbert ,  Nathan L. Messersmith ,  Christopher W. Robak

IPC: F01D11/02 ,  F01D11/00 ,  F01D11/08 ,  F16J15/44

Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.

公开(公告)号：US20200217216A1

公开(公告)日：2020-07-09

申请号：US16239616

申请日：2019-01-04

Applicant: United Technologies Corporation

Inventor： Eric A. Grover ,  Brian F. Hilbert ,  Nathan L. Messersmith ,  Christopher W. Robak

IPC: F01D11/00 ,  F01D11/08 ,  F16J15/44

Abstract: A hydrostatic seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a seal housing. The seal further includes a shoe operatively coupled to the base and extending axially from a forward end to an aft end. The seal yet further includes a plurality of teeth extending radially from a sealing surface of the shoe, one of the teeth being a longest tooth that extends furthest radially from the sealing surface, the axial distance from the forward end of the shoe to the longest tooth being greater than a radial distance from a radial tooth tip to the sealing surface.