EP0219721B1 - Einrichtung zur äusseren Ummantelung der Laufschaufeln von Axialgasturbinen - Google Patents

Einrichtung zur äusseren Ummantelung der Laufschaufeln von Axialgasturbinen Download PDF

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Publication number
EP0219721B1
EP0219721B1 EP86113379A EP86113379A EP0219721B1 EP 0219721 B1 EP0219721 B1 EP 0219721B1 EP 86113379 A EP86113379 A EP 86113379A EP 86113379 A EP86113379 A EP 86113379A EP 0219721 B1 EP0219721 B1 EP 0219721B1
Authority
EP
European Patent Office
Prior art keywords
ring
peripheral brush
bristles
brush
ceramic
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.)
Expired
Application number
EP86113379A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0219721A1 (de
Inventor
Hagen Hanser
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0219721A1 publication Critical patent/EP0219721A1/de
Application granted granted Critical
Publication of EP0219721B1 publication Critical patent/EP0219721B1/de
Expired legal-status Critical Current

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator

Definitions

  • the invention relates to a device for the outer sheathing of the rotor blades of axial gas turbines, with a closed ring consisting of ceramic material lying radially on the outside opposite the rotor blade tips, which is held in a metal turbine housing part by bristles that are at an angle to the radial direction and a peripheral brush that surrounds it, the bristles on Turbine housing part are attached.
  • a device of this type is known from GB-A 2 051 962. There the bristles of the peripheral brush are only attached on the housing side. As a result, the ring is not clearly positioned.
  • Devices of the aforementioned type have the advantage over conventional metallic turbine casing rings that, due to the high temperature resistance of the ceramic material, there is no need for structurally complex cooling devices.
  • DE-OS 2 737 622 the problem of different thermal expansion between ceramic wall parts and outer housings is attempted to be solved by dividing the ceramic wall parts into individual segment blocks which are freely stretchable in dovetail intermediate frames in corresponding housing chambers of the metal housing Turbine are stored.
  • the object of the present invention is to provide a device of the generic type which, on the one hand, has the advantageous properties of ceramic material, namely heat resistance, corrosion and erosion resistance, thereby ensuring secure centering and holding of the ceramic ring and, at the same time, is structurally simple and easy to maintain.
  • the main advantage of the device according to the invention is that due to the use of a peripheral brush with bristles fastened on both sides as the holding element, the ceramic ring is clearly positioned, the entire sheathing device being structurally simple.
  • the profile of the ceramic ring can have a simple regular contour, e.g. B. a rectangle.
  • the different thermal expansion between the ceramic ring on the one hand and the metal housing of the axial gas turbine on the other hand is compensated for by the peripheral brush, whereby very different thermal expansion between the ceramic ring and the metal housing does not result in an uncontrolled bending of the bristles, but causes a slight relative rotation of the ceramic ring with respect to the metal housing with the least bending of the bristles becomes.
  • the peripheral brush has metal bristles.
  • the use of metal bristles is advantageous because of the ductility that is present even at high temperatures.
  • they enable - what is proposed in a further embodiment of the invention - a comparatively problem-free connection technology by soldering both on the ceramic ring and on the metal housing.
  • An advantageous development of the invention is characterized in that a shield ring, which only leaves narrow annular gaps for the ceramic ring, engages over the brush in such a way that delimited annular spaces are formed on both sides of the brush, through which cooling air is guided.
  • This configuration serves in particular to protect the metallic bristles of the peripheral brush from excessive temperatures, but to consume only small amounts of cooling air.
  • the fact that closed annular spaces are created around the peripheral brush and the cooling air for the peripheral brush is passed through these annular spaces allows the cooling air throughput to be kept very low.
  • the amount of cooling air is of the order of 0.1% of the total amount of cooling air consumed for cooling the axial gas turbine or the gas turbine engine.
  • the axially flowed through rotor of a gas turbine shown in FIG. 1 has a rotor disk 7, in which a ring of axial blades 6 is anchored. Opposed to the blade tips 6a is a closed ring 1 made of ceramic material. The gap between the blade tips 6 a and the inner peripheral surface of the ring 1 is kept to a minimum. Silicon nitride or silicon carbide is preferably used as the material for the ring 1.
  • the ring 1 is centered and held in a metal housing 9 of the gas turbine in such a way that an annular peripheral brush 3 is fixed on the one hand in the metal housing 9 and on the other hand on the outer peripheral surface of the ring 1.
  • the bristles of the peripheral brush are made of metal and are fixed by soldering 4 a to an inner peripheral surface of the metal housing 9 and by soldering 4 b to an outer peripheral surface of the ceramic ring 1.
  • the metal housing 9 is formed in the area of the brush 3 as a shield ring 2 which engages over the brush 3 in such a way that annular spaces which are delimited on both sides are formed and are delimited on their radially inner side by the ceramic ring 1. Only narrow ring gaps 8 are left between the shield ring 2 and the ceramic ring 1. In the shield ring 2 are distributed over the circumference, 3 holes are provided on both sides of the brush, which serve on one side of the cooling air supply and on the other side of the brush 3 of the cooling air discharge.
  • the air duct is marked by arrows K.
  • the shield ring instead of the one-piece design of the shield ring 2 with the housing 9, the shield ring also be provided in the form of two separate flanges which are fastened to the housing 9 by suitable means.
  • FIG. 1 shows the inclined position of the bristles of the brush 3 by the angle y against the radial direction r.
  • the bores 5 serve to fasten the housing part 9, which is designed as a flange, to other modules of the axial gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP86113379A 1985-10-02 1986-09-29 Einrichtung zur äusseren Ummantelung der Laufschaufeln von Axialgasturbinen Expired EP0219721B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19853535106 DE3535106A1 (de) 1985-10-02 1985-10-02 Einrichtung zur aeusseren ummantelung der laufschaufeln von axialgasturbinen
DE3535106 1985-10-02

Publications (2)

Publication Number Publication Date
EP0219721A1 EP0219721A1 (de) 1987-04-29
EP0219721B1 true EP0219721B1 (de) 1989-04-19

Family

ID=6282527

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86113379A Expired EP0219721B1 (de) 1985-10-02 1986-09-29 Einrichtung zur äusseren Ummantelung der Laufschaufeln von Axialgasturbinen

Country Status (4)

Country Link
US (1) US4732534A (enExample)
EP (1) EP0219721B1 (enExample)
JP (1) JPH0650042B2 (enExample)
DE (2) DE3535106A1 (enExample)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8921003D0 (en) * 1989-09-15 1989-11-01 Rolls Royce Plc Improvements in or relating to shroud rings
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
US6733233B2 (en) * 2002-04-26 2004-05-11 Pratt & Whitney Canada Corp. Attachment of a ceramic shroud in a metal housing
DE10334698A1 (de) * 2003-07-25 2005-02-10 Rolls-Royce Deutschland Ltd & Co Kg Deckbandsegment für eine Strömungsmaschine
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
US12000296B2 (en) * 2022-02-22 2024-06-04 General Electric Company Seal for a rotor
US11879340B1 (en) 2022-09-30 2024-01-23 Rtx Corporation Angled brush seal and gas turbine engine component combination

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB859525A (en) * 1958-10-09 1961-01-25 Arnold Aaron Saul Rose Fluid seal
FR1339482A (fr) * 1961-11-28 1963-10-04 Licentia Gmbh Joint de rotor à segments annulaires d'étanchéité radialement mobiles, notammentpour turbo-moteurs
US3607600A (en) * 1969-07-15 1971-09-21 Hauck Mfg Co Composite molding process and product
GB1450553A (en) * 1973-11-23 1976-09-22 Rolls Royce Seals and a method of manufacture thereof
GB1484288A (en) * 1975-12-03 1977-09-01 Rolls Royce Gas turbine engines
US4087199A (en) * 1976-11-22 1978-05-02 General Electric Company Ceramic turbine shroud assembly
US4135851A (en) * 1977-05-27 1979-01-23 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Composite seal for turbomachinery
JPS5811934B2 (ja) * 1977-06-21 1983-03-05 高砂香料工業株式会社 メントンの製法
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
GB2051962B (en) * 1979-06-30 1982-12-15 Rolls Royce Turbine shroud ring support
FR2468741A1 (fr) * 1979-10-26 1981-05-08 Snecma Perfectionnements aux anneaux a joint d'etancheite refroidi par l'air pour roues de turbine a gaz
US4422648A (en) * 1982-06-17 1983-12-27 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
FR2548733B1 (fr) * 1983-07-07 1987-07-10 Snecma Dispositif d'etancheite d'aubages mobiles de turbomachine

Also Published As

Publication number Publication date
DE3535106A1 (de) 1987-04-16
US4732534A (en) 1988-03-22
JPH0650042B2 (ja) 1994-06-29
DE3662931D1 (en) 1989-05-24
EP0219721A1 (de) 1987-04-29
JPS62174504A (ja) 1987-07-31
DE3535106C2 (enExample) 1987-07-16

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