EP1645725A1 - Segment de virole pour un moteur à turbine - Google Patents

Segment de virole pour un moteur à turbine Download PDF

Info

Publication number
EP1645725A1
EP1645725A1 EP05254609A EP05254609A EP1645725A1 EP 1645725 A1 EP1645725 A1 EP 1645725A1 EP 05254609 A EP05254609 A EP 05254609A EP 05254609 A EP05254609 A EP 05254609A EP 1645725 A1 EP1645725 A1 EP 1645725A1
Authority
EP
European Patent Office
Prior art keywords
segment
hook
projection
shroud segment
shroud
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP05254609A
Other languages
German (de)
English (en)
Inventor
Toby George Darkins, Jr.
Mary Ellen Alford
Mark Eugen Noe
Christopher Charles Crissman
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1645725A1 publication Critical patent/EP1645725A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector

Definitions

  • This invention relates generally to turbine engine shroud segments including a surface exposed to elevated temperature engine gas flow. More particularly, it relates to air cooled gas turbine engine shroud segments, for example used in the turbine section of a gas turbine engine, and made of a low ductility material.
  • a turbine engine shroud segment is a stationary engine component separate and distinct from a component that includes an airfoil, for example a nozzle segment or a stationary blading member.
  • a plurality of stationary shroud segments is assembled circumferentially about an axial flow engine axis and radially about and spaced apart from rotating blading members, for example about rotating turbine blades. Together, such shroud segments define a part of the radial flowpath boundary over the blades.
  • Typical examples of U.S. Patents relating to turbine engine shrouds, shroud segments and such shroud clearance include 5,071,313 - Nichols; 5,074,748 - Hagle; 5,127,793 - Walker et al.; 5,562,408 - Proctor et al.; and 6,702,550 B2 - Darkins, Jr. et al.
  • the shroud segment In its function as a flowpath component, the shroud segment must be capable of meeting the design life requirements selected for use in a designed engine operating temperature and pressure environment. To enable current materials to operate effectively as a shroud segment in the strenuous temperature and pressure conditions as exist in the turbine section flowpath of modern gas turbine engines, it has been a practice to provide cooling air to an outer portion of the shroud segment. However as is well known in the art, for example as described in some of the above identified patents, provision of such cooling air is at the expense of engine efficiency. Therefore, it is desired to conserve use of cooling air by minimizing leakage into the flowpath of the engine of cooling air not intended to be introduced into the flowpath. For example, some forms of shroud segments include cooling passages intentionally to pass cooling air into the engine flow stream. However, cooling air leakage about edges of a shroud segment can reduce designed efficiency by wasting cooling airflow.
  • Chording results from a thermal differential or gradient between a higher temperature radially inner shroud surface and a lower temperature, air cooled shroud outer shroud surface. At least the radially inner or flowpath surface of a shroud and its segments are arced circumferentially to define a flowpath annular surface about the rotating tips of the blades. The thermal gradient between the inner and outer faces of the shroud, resulting from cooling air impingement on the outer surface, causes the arc of the shroud segments to chord or tend to straighten out circumferentially.
  • chording As a result of chording, the circumferential end portions of the inner surface of the shroud segment tend to move radially outwardly in respect to the middle portion of the segment. If allowed to occur, this type of action can increase the tip clearance required to prevent a rub between the blade and the shroud. As a shroud straightens from its original curvature, the shroud ends pull away from the intended flowpath and effectively increase the clearance of the blade. Therefore, for more efficient engine operation, it is desirable to restrain chording or seal the gap resulting from chording.
  • CMC ceramic matrix composite
  • CMC type materials have relatively low tensile ductility or low strain to failure when compared with metallic materials.
  • CMC type materials have a coefficient of thermal expansion (CTE) in the range of about 1.5 - 5 microinch/inch/°F, significantly different from commercial metal alloys used as restraining supports or hangers for shrouds of CMC type materials.
  • Such metal alloys typically have a CTE in the range of about 7 - 10 microinch/inch/°F. Therefore, if a CMC type of shroud segment is restrained and cooled on one surface during operation, forces or stresses can be developed in CMC type segment sufficient to cause failure of the segment or its integral attachment system.
  • CMC materials include a ceramic type fiber for example SiC, forms of which are coated with a compliant material such as BN. The fibers are carried in a ceramic type matrix, one form of which is SiC.
  • CMC type materials have a room temperature tensile ductility of no greater than about 1%, herein used to define and mean a low tensile ductility material.
  • CMC type materials have a room temperature tensile ductility in the range of about 0.4 - 0.7%. This is compared with metallic shroud and/or supporting structure or hanger materials having a room temperature tensile ductility of at least about 5%, for example in the range of about 5 - 15%.
  • Shroud segments made from CMC type materials although having certain higher temperature capabilities than those of a metallic type material, cannot tolerate the above described and currently used type of compressive force or similar restraint force against chording. Neither can they withstand a stress rising type of feature, for example one provided at a relatively small bent or filleted surface area, without sustaining damage or fracture typically experienced by ceramic type materials. Furthermore, manufacture of articles from CMC materials limits the bending of the SiC fibers about such a relatively tight fillet to avoid fracture of the relatively brittle ceramic type fibers in the ceramic matrix.
  • the present invention provides a shroud segment for use in a turbine engine, for example in a gas turbine engine turbine shroud assembly, comprising a body including a body inner surface and a body outer surface spaced apart from the body inner surface.
  • the body extends between spaced-apart body first and second axial edge portions and spaced-apart body first and second circumferential edge portions.
  • the shroud segment includes an attachment system comprising projection hooks, for carrying the shroud segment, integral with and projecting away from the body outer surface.
  • Each projection hook comprises a hook arm extending away from the body outer surface and a hook end portion extending axially and including a segment support surface of selected support surface shape facing toward the body outer surface.
  • a plurality of individual, discrete projection hook segments are in at least two axially spaced-apart circumferentially extending rows defining the attachment system.
  • Each row comprises a plurality of the discrete projection hook segments spaced-apart circumferentially along the body outer surface at least partially between the first and second circumferential edge portions.
  • Each hook end portion of each projection hook segment in a row faces an axial edge portion, and each segment support surface of each projection hook is aligned circumferentially and radially with other segment support surfaces in a row.
  • Such an engine comprises, in serial flow communication generally from forward to aft, one or more compressors, a combustion section, and one or more turbine sections disposed axisymmetrically about a longitudinal engine axis.
  • phrases using the term “axially”, for example “axially forward” and “axially aft”, refer to relative positions or general directions in respect to the engine axis; phrases using forms of the term “circumferential” refer to circumferential position or direction generally about the engine axis; and phrases using forms of the term “radial”, for example “radially inner” and “radially outer”, refer to relative radial position or direction generally from the engine axis.
  • FIG. 1 is a diagrammatic perspective view of an embodiment of a turbine engine shroud segment according to the present invention.
  • Such embodiment includes an attachment system that enables carrying of a shroud segment, made of the above described low ductility materials such as a CMC, in a turbine engine shroud assembly without application or development of excessive pressure or force to the shroud segment, including excessive hoop stresses.
  • a shroud segment shown generally at 10 includes a shroud segment body, shown generally at 12, having a body radially inner surface 14 and a body radially outer surface 16 spaced apart from radially inner surface 14.
  • Body 12 extends between spaced apart first and second axial edge portions, respectively 18 and 20, and first and second circumferential edge portions, respectively 22 and 24.
  • Shroud segment 10 includes a plurality of individual, discrete projection hook segments, shown generally at 26, integral with and extending generally away from body radially outer surface 16.
  • projection hook segments 26 comprise a shroud segment attachment system that severs a potential hoop stress path through such system.
  • projection hook segments 26 are spaced-apart and aligned circumferentially along body outer surface 16 in a plurality of axially spaced-apart, circumferentially extending rows of projection hook segments.
  • such rows comprising the integral attachment system are shown generally at 28 and 30.
  • each projection hook segment 26 comprises a hook segment arm 32 extending away from body outer surface 16 and a hook segment end portion 34 extending generally axially toward an axial edge portion 18 or 20.
  • Hook segment end portion 34 includes a segment support surface 36 facing toward body outer surface 16 and of a selected support surface shape, for example planar or arcuate.
  • segment support surfaces 36 of projection hook segments 26 in a circumferential row, for example in row 28 and in row 30, are aligned circumferentially and radially one with another in the row. Segment support surface 36 is shown more clearly in Figures 2, 3 and 5.
  • all hook segment end portions 34 face toward segment body second axial edge portion 20.
  • the terms “toward” or “away from” in respect to a surface direction means generally and predominantly in the direction with respect to such surface or member.
  • orientation of shroud segment 10 and its attachment system comprising a plurality of circumferential rows of projection hook segments are shown in respect to a turbine engine by arrows 38, 40 and 42 representing, respectively, the engine circumferential, axial, and radial directions.
  • Figure 2 is another diagrammatic view of the embodiment of Figure 1, along lines 2-2, toward circumferential edge portion 22 of shroud segment 10 of Figure 1.
  • Figure 2 shows projection hook segments 26 in circumferential row 28 and in circumferential row 30 spaced-apart in axial direction 40 with their segment support surfaces 36 aligned respectively in circumferential direction 38 and radial direction 42.
  • segment support surfaces are shown to have a planar selected support surface shape.
  • Figure 3 is a diagrammatic view, similar to Figure 2 and based on a shroud segment as described in connection with Figure 1, toward a circumferential edge portion 22 of another embodiment of a shroud segment according to the present invention.
  • a plurality of projection hook segments 26 is circumferentially spaced-apart in three circumferentially extending rows represented by 28, 44 and 30, respectively spaced-apart in axial direction 40 aft along body radially outer surface 16.
  • projection hook segments 26 in a circumferential row are spaced-apart in circumferential direction 38, with their segment support surfaces aligned in circumferential direction 38 and in radial direction 42.
  • all hook end portions 34 face toward second axial edge portion 20.
  • Figure 4 is a diagrammatic, perspective, partially fragmentary view of still another embodiment according to the present invention, including two axially spaced-apart, circumferentially extending rows, first row 28 and second row 46, of circumferentially spaced-apart projection hook segments 26.
  • hook end portions 34 of projection hook segments 26 in circumferential first row 28 face toward second axial edge portion 20 while hook end portions 34 of projection hook segments 26 in circumferential second row 46 face toward first axial edge portion 18.
  • segment support surfaces 36 in a row are aligned one with another in circumferential direction 38 and in radial direction 42.
  • FIG. 5 The diagrammatic, fragmentary view of Figure 5 is of a shroud segment, similar to that in Figure 1 and viewed aft of shroud segment 10 from axial direction 40, assembled circumferentially adjacent other shroud segments (not shown) as is typical in a turbine engine shroud assembly, circumferentially about engine axis 48.
  • the shape of segment support surfaces 36 of each projection hook 26 in a circumferential row is selected to be an arc along a circle, shown in phantom as 50, with radius 52 about engine axis 48.
  • the present invention provides a shroud segment including an integral attachment system that interrupts a potentially damaging, substantially continuous hoop stress path through the attachment system, enabling use in a turbine engine of a shroud segment made of a low ductility material.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05254609A 2004-10-08 2005-07-25 Segment de virole pour un moteur à turbine Withdrawn EP1645725A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/962,310 US20060078429A1 (en) 2004-10-08 2004-10-08 Turbine engine shroud segment

Publications (1)

Publication Number Publication Date
EP1645725A1 true EP1645725A1 (fr) 2006-04-12

Family

ID=35614695

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05254609A Withdrawn EP1645725A1 (fr) 2004-10-08 2005-07-25 Segment de virole pour un moteur à turbine

Country Status (3)

Country Link
US (1) US20060078429A1 (fr)
EP (1) EP1645725A1 (fr)
JP (1) JP2006105129A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104564821A (zh) * 2013-10-14 2015-04-29 哈米尔顿森德斯特兰德公司 冲压空气风机外壳

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5517742B2 (ja) * 2010-05-21 2014-06-11 三菱重工業株式会社 分割体、これを用いたタービン分割環およびこれを備えたガスタービン
US8905709B2 (en) * 2010-09-30 2014-12-09 General Electric Company Low-ductility open channel turbine shroud
US8998565B2 (en) 2011-04-18 2015-04-07 General Electric Company Apparatus to seal with a turbine blade stage in a gas turbine
US20130004306A1 (en) * 2011-06-30 2013-01-03 General Electric Company Chordal mounting arrangement for low-ductility turbine shroud
US9726043B2 (en) 2011-12-15 2017-08-08 General Electric Company Mounting apparatus for low-ductility turbine shroud
US9464536B2 (en) 2012-10-18 2016-10-11 General Electric Company Sealing arrangement for a turbine system and method of sealing between two turbine components
CN105612313B (zh) 2013-05-17 2017-11-21 通用电气公司 燃气涡轮机的cmc护罩支撑系统
EP3080403B1 (fr) 2013-12-12 2019-05-01 General Electric Company Système de support de carénage cmc
WO2015191169A1 (fr) 2014-06-12 2015-12-17 General Electric Company Ensemble de suspension de carénage
WO2015191174A1 (fr) 2014-06-12 2015-12-17 General Electric Company Ensemble dispositif de suspension de carénage à multiples pièces
EP3155231B1 (fr) 2014-06-12 2019-07-03 General Electric Company Ensemble dispositif de suspension de carénage
JP5717904B1 (ja) * 2014-08-04 2015-05-13 三菱日立パワーシステムズ株式会社 静翼、ガスタービン、分割環、静翼の改造方法、および、分割環の改造方法
US9874104B2 (en) 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
KR101937586B1 (ko) * 2017-09-12 2019-01-10 두산중공업 주식회사 베인 조립체, 터빈 및 이를 포함하는 가스터빈
US20190218928A1 (en) * 2018-01-17 2019-07-18 United Technologies Corporation Blade outer air seal for gas turbine engine
US11286801B2 (en) * 2018-10-12 2022-03-29 Raytheon Technologies Corporation Boas with twin axial dovetail
US11519283B2 (en) * 2021-03-25 2022-12-06 Raytheon Technologies Corporation Attachment region for CMC components

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5071313A (en) 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
US5074748A (en) 1990-07-30 1991-12-24 General Electric Company Seal assembly for segmented turbine engine structures
US5127793A (en) 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
US5562408A (en) 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud
EP0959229A2 (fr) * 1998-05-19 1999-11-24 General Electric Company Segment de virole à tension réduite pour turbines
EP1178182A1 (fr) * 2000-03-07 2002-02-06 Mitsubishi Heavy Industries, Ltd. Anneau fendu de turbine a gaz
US6602050B1 (en) * 1999-03-24 2003-08-05 Siemens Aktiengesellschaft Covering element and arrangement with a covering element and a support structure
US6702550B2 (en) 2002-01-16 2004-03-09 General Electric Company Turbine shroud segment and shroud assembly
US20040062639A1 (en) * 2002-09-30 2004-04-01 Glynn Christopher Charles Turbine engine shroud assembly including axially floating shroud segment
US6726391B1 (en) * 1999-08-13 2004-04-27 Alstom Technology Ltd Fastening and fixing device

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
US3807891A (en) * 1972-09-15 1974-04-30 United Aircraft Corp Thermal response turbine shroud
GB1484936A (en) * 1974-12-07 1977-09-08 Rolls Royce Gas turbine engines
US3966353A (en) * 1975-02-21 1976-06-29 Westinghouse Electric Corporation Ceramic-to-metal (or ceramic) cushion/seal for use with three piece ceramic stationary vane assembly
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
US5441385A (en) * 1993-12-13 1995-08-15 Solar Turbines Incorporated Turbine nozzle/nozzle support structure
US5439348A (en) * 1994-03-30 1995-08-08 United Technologies Corporation Turbine shroud segment including a coating layer having varying thickness
US5486090A (en) * 1994-03-30 1996-01-23 United Technologies Corporation Turbine shroud segment with serpentine cooling channels
US5423659A (en) * 1994-04-28 1995-06-13 United Technologies Corporation Shroud segment having a cut-back retaining hook
US5480281A (en) * 1994-06-30 1996-01-02 General Electric Co. Impingement cooling apparatus for turbine shrouds having ducts of increasing cross-sectional area in the direction of post-impingement cooling flow
US5653581A (en) * 1994-11-29 1997-08-05 United Technologies Corporation Case-tied joint for compressor stators
US5609469A (en) * 1995-11-22 1997-03-11 United Technologies Corporation Rotor assembly shroud
DE19936761A1 (de) * 1999-08-09 2001-05-10 Abb Alstom Power Ch Ag Befestigungsvorrichtung für Hitzeschutzschilde
US6733235B2 (en) * 2002-03-28 2004-05-11 General Electric Company Shroud segment and assembly for a turbine engine
US6758653B2 (en) * 2002-09-09 2004-07-06 Siemens Westinghouse Power Corporation Ceramic matrix composite component for a gas turbine engine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5071313A (en) 1990-01-16 1991-12-10 General Electric Company Rotor blade shroud segment
US5127793A (en) 1990-05-31 1992-07-07 General Electric Company Turbine shroud clearance control assembly
US5074748A (en) 1990-07-30 1991-12-24 General Electric Company Seal assembly for segmented turbine engine structures
US5562408A (en) 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud
EP0959229A2 (fr) * 1998-05-19 1999-11-24 General Electric Company Segment de virole à tension réduite pour turbines
US6602050B1 (en) * 1999-03-24 2003-08-05 Siemens Aktiengesellschaft Covering element and arrangement with a covering element and a support structure
US6726391B1 (en) * 1999-08-13 2004-04-27 Alstom Technology Ltd Fastening and fixing device
EP1178182A1 (fr) * 2000-03-07 2002-02-06 Mitsubishi Heavy Industries, Ltd. Anneau fendu de turbine a gaz
US6702550B2 (en) 2002-01-16 2004-03-09 General Electric Company Turbine shroud segment and shroud assembly
US20040062639A1 (en) * 2002-09-30 2004-04-01 Glynn Christopher Charles Turbine engine shroud assembly including axially floating shroud segment

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104564821A (zh) * 2013-10-14 2015-04-29 哈米尔顿森德斯特兰德公司 冲压空气风机外壳
US9914542B2 (en) 2013-10-14 2018-03-13 Hamilton Sundstrand Corporation Ram air fan housing
CN104564821B (zh) * 2013-10-14 2019-10-08 哈米尔顿森德斯特兰德公司 冲压空气风机外壳

Also Published As

Publication number Publication date
JP2006105129A (ja) 2006-04-20
US20060078429A1 (en) 2006-04-13

Similar Documents

Publication Publication Date Title
EP1645725A1 (fr) Segment de virole pour un moteur à turbine
EP1643084B1 (fr) Segment de virole pour une moteur à turbine et dispositif de suspension
EP1350927B1 (fr) Segment de virole, procédé de fabrication d'un segment de virole, et virole pour moteur à turbine
US6702550B2 (en) Turbine shroud segment and shroud assembly
US6884026B2 (en) Turbine engine shroud assembly including axially floating shroud segment
US6808363B2 (en) Shroud segment and assembly with circumferential seal at a planar segment surface
JP6184042B2 (ja) 熱応力の無いファスナーを用いたタービン構成要素の接続装置
US8079807B2 (en) Mounting apparatus for low-ductility turbine shroud
EP1431518A2 (fr) Ensemble de segments de virole d'une turbine à gaz avec un élément d'étanchéité entre chaque segment
US9518474B2 (en) Continuous ring composite turbine shroud
US8740552B2 (en) Low-ductility turbine shroud and mounting apparatus
EP2540994B1 (fr) Agencement pour le montage d'anneau de turbine à faible ductilité
US10822973B2 (en) Shroud for a gas turbine engine
WO2015002673A2 (fr) Ensemble joint pour moteur à turbine à gaz
JP2007046605A (ja) 熱的にコンプライアントなタービンシュラウドアセンブリ

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20061012

17Q First examination report despatched

Effective date: 20061113

AKX Designation fees paid

Designated state(s): DE FR GB IT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20130823

RIN1 Information on inventor provided before grant (corrected)

Inventor name: CRISSMAN, CHRISTOPHER CHARLES

Inventor name: ALFORD, MARY ELLEN

Inventor name: DARKINS, TOBY GEORGE, JR.

Inventor name: NOE, MARK EUGEN

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140103