公开(公告)号：NO20050747D0

公开(公告)日：2005-02-11

申请号：NO20050747

申请日：2005-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  PROPHETER TRACY

IPC: F01D5/10 ,  F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F01D5/30 ,  F04D29/38 ,  F04D29/66 ,  F03B

Abstract: A rotor blade (12) for a rotor assembly (9) is provided that includes a root (18), an airfoil (20), a platform (22), and a damper (24). The airfoil (20) has at least one cavity (44). The platform (22) is disposed between the root (18) and the airfoil (20). The platform (22) includes an inner surface (58), an outer surface (56), and a damper aperture (60) disposed in the inner surface (58). The damper (24) has a body (62) and a base (64). The base (64) and the damper aperture (60) have mating geometries that enable the base (64) to rotate within the damper aperture (60) without substantial impediment from the mating geometries.

公开(公告)号：AU2005201263A1

公开(公告)日：2005-12-15

申请号：AU2005201263

申请日：2005-03-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： PROPHETER TRACY ,  SURACE RAYMOND

IPC: F01D5/10 ,  F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F01D5/16 ,  F01D5/26 ,  F16F15/12

Abstract: A rotor blade damper (48) is provided that includes a body (58) having a base (60), a tip (62), a first contact surface (64), a second contact surface (66), a trailing edge surface (68), and a leading edge surface (70). The trailing edge and the leading edge surfaces (68,70) extend between the contact surfaces (64,66). The first contact surface (64), second contact surface (66), trailing edge surface (68), and leading edge surface (70) all extend lengthwise between the base (60) and the tip (62). The body (58) includes at least one cooling aperture (82) disposed adjacent the base (60), that has a diameter that is approximately equal to or greater than the width of the trailing edge surface (68) adjacent the tip (62). The body (58) tapers between the base (60) and the tip (62) such that a first widthwise cross-sectional area adjacent the base (60) is greater than a second widthwise cross-sectional area adjacent the tip (62).

公开(公告)号：NO20050747L

公开(公告)日：2005-08-15

申请号：NO20050747

申请日：2005-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  PROPHETER TRACY

IPC: F01D5/10 ,  F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F01D5/30 ,  F04D29/38 ,  F04D29/66 ,  F01D5/12 ,  F01D5/00

Abstract: A rotor blade (12) for a rotor assembly (9) is provided that includes a root (18), an airfoil (20), a platform (22), and a damper (24). The airfoil (20) has at least one cavity (44). The platform (22) is disposed between the root (18) and the airfoil (20). The platform (22) includes an inner surface (58), an outer surface (56), and a damper aperture (60) disposed in the inner surface (58). The damper (24) has a body (62) and a base (64). The base (64) and the damper aperture (60) have mating geometries that enable the base (64) to rotate within the damper aperture (60) without substantial impediment from the mating geometries.

公开(公告)号：NO20050747A

公开(公告)日：2005-08-15

申请号：NO20050747

申请日：2005-02-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  PROPHETER TRACY

IPC: F01D5/10 ,  F01D5/16 ,  F01D5/18 ,  F01D5/26 ,  F01D5/30 ,  F04D29/38 ,  F04D29/66 ,  F01D5/00 ,  F01D5/12

CPC classification number: F01D5/26 ,  F01D5/16 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/30 ,  Y10S416/50

公开(公告)号：AU2004214543A1

公开(公告)日：2005-04-28

申请号：AU2004214543

申请日：2004-09-24

Applicant: UNITED TECHNOLOGIES CORP

Inventor： COLON DENNIS I ,  SURACE RAYMOND

IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00 ,  F04D29/08 ,  F04D29/38 ,  F02C7/28 ,  F01D5/00

Abstract: A turbomachine blade damper has a damper member (52) with first and second (58,60) damping surfaces for respectively engaging first and second surfaces of adjacent first and second blades (20). The damper has a seal (70) having a first portion (22) engaged in the damper member (58) to resist relative movement of the seal in at least one direction and a second portion (74) engaging at least one of the blades and advantageously forming a seal to resist upstream gas infiltration.

公开(公告)号：NO20044251A

公开(公告)日：2005-04-11

申请号：NO20044251

申请日：2004-10-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  COLON DENNIS I

IPC: F01D5/26 ,  F01D5/22 ,  F01D11/00 ,  F04D29/08 ,  F04D29/38 ,  F01D5/10 ,  F01D5/00 ,  F02C6/12

CPC classification number: F01D11/008 ,  F01D5/22 ,  F05D2230/60 ,  F05D2260/30 ,  Y10S416/50

公开(公告)号：NO20050623D0

公开(公告)日：2005-02-04

申请号：NO20050623

申请日：2005-02-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  GREGG SHAWN J ,  PROPHETER TRACY ,  OTERO EDWIN

IPC: F01D5/10 ,  F01D5/16 ,  F01D5/18 ,  F01D25/06 ,  F01D

Abstract: A rotor blade (14) for a rotor assembly (10) is provided that includes a root (18), an airfoil (20), and a damper (24). The airfoil (20) has a length, a base (28), a tip (30), a first side wall (36,38), a second side wall (38,36), and at least one cavity (40). The length extends the base (28) and the tip (30). The at least one cavity (40) is disposed between the side walls (36,38), and the channel (42) is defined by a first wall portion (54) and a second wall portion (56). The damper (24), which is selectively received within the channel (42), includes a first bearing surface (80), a second bearing surface (82), a forward surface (76), and an aft surface (78), all of which extend lengthwise. At least one of the surfaces is shaped to form a lengthwise extending passage (92) within the channel (42). The passage (92) has a flow direction oriented along the length of the at least one surface to permit cooling air travel along the at least one surface in a lengthwise direction. According to one aspect of the present invention, the damper (24) has an arcuate lengthwise extending centerline (71).

公开(公告)号：EP3036404A4

公开(公告)日：2017-03-22

申请号：EP14837668

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SURACE RAYMOND ,  HUDSON ERIC A

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F02C7/042 ,  F02C7/18 ,  F04D29/58

CPC classification number: F01D17/162 ,  F01D9/065 ,  F01D11/24 ,  F01D17/16 ,  F02C7/12 ,  F05D2260/205

Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.

公开(公告)号：EP2948642A4

公开(公告)日：2016-05-25

申请号：EP13872458

申请日：2013-01-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MCCAFFREY MICHAEL G ,  PROPHETER-HINCKLEY TRACY A ,  SURACE RAYMOND ,  SPANGLER BRANDON W

IPC: F01D17/16 ,  F01D5/14 ,  F01D9/04 ,  F01D9/06 ,  F02C9/22

CPC classification number: F01D17/16 ,  F01D5/147 ,  F01D9/04 ,  F01D9/065 ,  F01D17/162 ,  F02C9/22 ,  F05D2260/201 ,  F05D2260/202

Abstract: An assembly for a turbine engine includes a plurality of vane segments. The vane segments are fastened together and form an adjustable stator vane that pivots about a variable vane axis. The adjustable stator vane includes a stator vane body, a shaft and a flange. The stator vane body extends axially between a first end and a second end, and includes an airfoil, a body surface and a cavity. The body surface is located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially at least partially around the inlet, and radially from the stator vane body. A first of the vane segments includes the flange. A second of the vane segments includes at least a portion of the airfoil.

公开(公告)号：EP3090146A4

公开(公告)日：2017-10-18

申请号：EP14878556

申请日：2014-11-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： TEIXEIRA JOHN D ,  SLAVENS THOMAS N ,  SURACE RAYMOND

IPC: F01D25/12 ,  F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D9/06 ,  F01D17/16

CPC classification number: F01D17/162 ,  F01D5/186 ,  F01D9/041 ,  F01D9/065 ,  F01D25/12 ,  F04D29/056 ,  F04D29/563 ,  F04D29/582 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/20

Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.