公开(公告)号：EP0808413B1

公开(公告)日：1998-11-25

申请号：EP96903460.2

申请日：1996-01-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： THOMPSON, Ralph, J. ,  KANE, Daniel, E. ,  SUNSHINE, Robert, W.

IPC: F01D25/12 ,  F01D11/08

CPC classification number: F01D11/08 ,  F01D25/12

Abstract: A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel having a bend passage which includes a purge hole to avoid separating flow in the bend passage.

公开(公告)号：EP0753100A1

公开(公告)日：1997-01-15

申请号：EP95914151.0

申请日：1995-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： THOMPSON, Ralph, J. ,  KANE, Daniel, E.

IPC: F01D11 ,  F01D25 ,  F02C7

CPC classification number: F01D11/08 ,  F01D25/12 ,  Y02T50/675

Abstract: A turbine shroud segment (64) fixed by hooks (72) in the stator of a gas turbine engine includes a serpentine cooling channel (78, 82) along at least one axial edge of the segment. In a particular embodiment, a turbine shroud segment (64) includes a leading edge serpentine cooling channel (78) and a trailing edge serpentine cooling channel (82). Both serpentine channels (78, 82) include ducts (86, 92) that extend to the serpentine channels (78, 82) from a point inward of adjacent retaining hooks (72). Cooling fluid flowing onto the outward surface of the segments flows through the ducts (86, 92) and along the serpentine channels (78, 82) to cool the leading and trailing edges of the segments.

公开(公告)号：EP0682741B1

公开(公告)日：1996-09-11

申请号：EP94908714.2

申请日：1994-02-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： KANE, Daniel, E. ,  HADDAD, Donald, E.

IPC: F01D11/08 ,  F01D11/00

CPC classification number: F01D11/08 ,  F01D11/005

Abstract: A coolable outer air seal assembly (38) for a gas turbine engine (12) is disclosed. Various construction details are developed which provide an outer air seal assembly (38) comprised of a plurality of seal segments (46) including bumpers (62) adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments (46). In one particular embodiment, each seal segment (46) includes a mating surface (64) having a plurality of bumpers (62) disposed adjacent to cooling fluid channel (58) outlets (72) and an axially extending ridge (88) disposed along the radially outer edge of the mating surface (64). The bumpers (62) extend circumferentially a distance Hb to maintain a minimum opening Gmin between adjacent seal segments (46) and extend a radial distance Wb to restrict fluid from flowing axially through the clearance gap. The ridge (88) extends radially outward to define in part a seal edge for engaging a feather seal (98).

公开(公告)号：EP0753100B1

公开(公告)日：1998-04-29

申请号：EP95914151.6

申请日：1995-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： THOMPSON, Ralph, J. ,  KANE, Daniel, E.

IPC: F01D11/08 ,  F01D25/12

CPC classification number: F01D11/08 ,  F01D25/12 ,  Y02T50/675

Abstract: A turbine shroud segment (64) fixed by hooks (72) in the stator of a gas turbine engine includes a serpentine cooling channel (78, 82) along at least one axial edge of the segment. In a particular embodiment, a turbine shroud segment (64) includes a leading edge serpentine cooling channel (78) and a trailing edge serpentine cooling channel (82). Both serpentine channels (78, 82) include ducts (86, 92) that extend to the serpentine channels (78, 82) from a point inward of adjacent retaining hooks (72). Cooling fluid flowing onto the outward surface of the segments flows through the ducts (86, 92) and along the serpentine channels (78, 82) to cool the leading and trailing edges of the segments.

公开(公告)号：EP0623189B1

公开(公告)日：1997-04-02

申请号：EP94902351.9

申请日：1993-11-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： STAHL, Matthew 700 Dominik Drive ,  HASTINGS, William, J. ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  DIERBERGER, James, A.

IPC: F01D11/08

CPC classification number: F01D11/122 ,  F05D2260/201 ,  F05D2260/202

Abstract: An outer air seal assembly (44) cooled by a combination of impingement cooling and film cooling is disclosed. Various construction details are developed which provide impingement of cooling fluid on a radially outer side of an outer air seal assembly (44) and ejection of a film of cooling fluid over a radially inner surface (52) of the outer air seal assembly (44). In a particular embodiment, an outer air seal assembly (44) includes a substrate (54), an apertured cover (56) disposed outward of the substrate (54), and a layer of abradable material (58) extending radially inward of the substrate (54) and defining a flow surface (52). Cooling fluid is directed through the apertures (72), into a cavity (66), and impinges upon the outer surface of the substrate (54). A plurality of film cooling holes (76) extend through the substrate (54) and abradable layer (58) and provide fluid communication between the cavity (66) and flowpath (14). The cooling holes (76) are oriented to eject cooling in a film over the flow surface (52). In another embodiment, the cavity (66) includes a longitudinally extending chamber (112) disposed in an enlarged portion (108) of the air seal (46) to enhance cooling thereof and reduce stresses therewithin.

公开(公告)号：EP0682741A1

公开(公告)日：1995-11-22

申请号：EP94908714.0

申请日：1994-02-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： KANE, Daniel, E. ,  HADDAD, Donald, E.

IPC: F01D11

CPC classification number: F01D11/08 ,  F01D11/005

Abstract: A coolable outer air seal assembly (38) for a gas turbine engine (12) is disclosed. Various construction details are developed which provide an outer air seal assembly (38) comprised of a plurality of seal segments (46) including bumpers (62) adapted to maintain adequate cooling fluid flow through the clearance gap between adjacent seal segments (46). In one particular embodiment, each seal segment (46) includes a mating surface (64) having a plurality of bumpers (62) disposed adjacent to cooling fluid channel (58) outlets (72) and an axially extending ridge (88) disposed along the radially outer edge of the mating surface (64). The bumpers (62) extend circumferentially a distance Hb to maintain a minimum opening Gmin between adjacent seal segments (46) and extend a radial distance Wb to restrict fluid from flowing axially through the clearance gap. The ridge (88) extends radially outward to define in part a seal edge for engaging a feather seal (98).

公开(公告)号：EP0623189A1

公开(公告)日：1994-11-09

申请号：EP94902351.0

申请日：1993-11-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： STAHL, Matthew 700 Dominik Drive ,  HASTINGS, William, J. ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  DIERBERGER, James, A.

IPC: F01D11 ,  F02C7

CPC classification number: F01D11/122 ,  F05D2260/201 ,  F05D2260/202

Abstract: L'invention concerne un ensemble d'étanchéité d'air externe (44) refroidi par refroidissements à choc et pelliculaire combinés. Plusieurs caractéristiques de construction sont présentées dont la projection du fluide de refroidissement contre un côté radialement externe d'un ensemble d'étanchéité d'air externe (44) et l'éjection d'un film de fluide de refroidissement sur une surface radialement interne (52) de l'ensemble d'étanchéité d'air externe (44). Dans un mode particulier de réalisation, un ensemble d'étanchéité d'air externe (44) est constitué d'un substrat (54), d'une couche à ouvertures (56) placée à l'extérieur du substrat (54), et d'une couche de matériau abrasable (58) s'étendant radialement vers l'intérieur du substrat (54) et définissant une surface d'écoulement (52). Le fluide de refroidissement est acheminé dans une cavité (66) par des ouvertures (72), et vient heurter la surface externe du substrat (54). Une pluralité d'orifices de refroidissement pelliculaire (70) qui s'étend à travers le substrat (54) et la couche abrasable (58), assure une communication fluidique entre la cavité (66) et la voie d'écoulement (14). Lesdits orifices de refroidissement (76) sont orientés de manière à éjecter le liquide de refroidissement sous forme pelliculaire sur la surfce d'écoulement (52). Dans un autre mode de réalisation, la cavité (66) comprend une chambre (112) s'étendant longitudinalement, située dans une partie évasée (108) de l'étanchéité d'air (46) afin d'en améliorer le refroidissement et de réduire les contraintes à l'intérieur de celle-ci.

公开(公告)号：EP1910648A2

公开(公告)日：2008-04-16

申请号：EP06788634.1

申请日：2006-07-28

Applicant: United Technologies Corporation

Inventor： PEZZETTI, Michael, C. ,  FAUCHER, Peter, A. ,  KANE, Daniel, E. ,  GOOD, Randall, R.

IPC: F01D11/00 ,  F01D11/08 ,  F01D25/24

CPC classification number: F01D11/005 ,  F01D11/08 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/57

Abstract: A stator assembly for a rotary machine having an array of wall segments for bounding a working medium flow path is disclosed. Various construction details which provide a sealing structure for the segments are developed. In one detailed embodiment, a removable seal retainer for a seal chamber bounded by wall segments traps a resilient seal member in the seal chamber. In one particular embodiment, a modular subassembly for the engine is an outer air assembly disposed in a fixture as the subassembly is assembled.

公开(公告)号：EP1872296A2

公开(公告)日：2008-01-02

申请号：EP06849734.6

申请日：2006-03-17

Applicant: United Technologies Corporation

Inventor： KANE, Daniel, E.

IPC: G06F19/00

CPC classification number: F01D11/20 ,  F01D11/24 ,  F05D2270/301 ,  F05D2270/702

Abstract: The invention is a method for controlling blade tip clearance in a turbine engine having a flowpath extending therethrough, and a system for carrying out the method. The method includes acquiring a first nonpulsating pressure signal Pc representative of tip clearance, sensing a second pressure PB substantially unaffected by tip clearance, forming an actual ratio of the acquired pressure and the sensed pressure, determining an error E having an actual component and a desired component, the actual component being a function of the actual ratio; and commanding a clearance control system to reduce the error.

公开(公告)号：EP0725888B1

公开(公告)日：2000-04-19

申请号：EP94926491.5

申请日：1994-08-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： STAHL, Matthew ,  KANE, Daniel, E. ,  MURDOCK, James, R. ,  HADDAD, Donald, E.

IPC: F01D11/08 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D25/246 ,  F01D11/005 ,  F01D11/08

Abstract: A shroud segment (42) for a gas turbine engine (12) includes a rail (54) engaged with adjacent support structure (52) to retain the segment (42) and to provide sealing between the segment (42) and the adjacent structure (52). The segment (42) is pressed against its support structure (52) by a resilient element (68) to provide effective sealing and retaining permitting differing thermal growth between the segment (42) and the support structure (52). In a particular embodiment, a shroud segment (42) includes a rail (54) along a forward edge. The rail (54) is engaged with a recess in the support structure (52) to retain the segment (42) and with a band (68) which positions the segment (42) and seals the forward edge.