Turbine ring for a gas turbine engine

• US 4,679,981 A
• Filed: 11/15/1985
• Issued: 07/14/1987
• Est. Priority Date: 11/22/1984
• Status: Expired due to Term

• Current Assignee: Snecma (Safran SA)
• Original Assignee: Snecma (Safran SA)
• Inventors: Ritt, Remy P. C., Guibert, Alain J. E., Mestre, Roland R.
• Primary Examiner(s): Garrett, Robert E.
• Assistant Examiner(s): Kwon, John
• Application Number:
  US06/798,318
• Time in Patent Office: 606 Days
• Field of Search: 415/134, 415/136, 415/137, 415/138, 415/116, 415/175, 415/170, 415/174, 415/197, 415/115, 415/171
• US Class Current: 415/116
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20

Abstract

A turbine ring has an annular metallic carrier which is mounted within the inside of the turbine casing and within the carrier there is provided a ceramic abradable ring. A cooling air circuit is provided to regulate the temperature of only the annular carrier such that the latter always exerts a centripetal compression force on the ring under all operational conditions of the gas turbine to clamp the abradable ring.

Claims

1. A turbine ring for a gas turbine comprising:

a turbine casing;

an annular metallic carrier mounted within the casing;

a one-piece ring of ceramic abradable material mounted within the annular carrier, said carrier having means for reducing heat transfer from said ceramic ring to said carrier and means for applying a compression force to the ceramic ring under all operational phases of the gas turbine;

means connected to a bleed of a compressor of said gas turbine for supplying cooling fluid to the annular carrier; and

means for regulating the supply of cooling fluid to the annular carrier, whereby only the temperature of the annular carries is controlled,

wherein said means for reducing heat transfer includes means for providing a small cross-section of contact between said ceramic ring and said carrier, said means for providing a small area of contact comprising a plurality of projections which extend radially between juxtaposed surfaces of the ceramic ring and the annular carrier, and

wherein said means for suppying cooling fluid to the annular carrier lacks means to cool directly other parts of the turbine ring and comprises;

(a) fluid distribution chamber means defined by the turbine casing and an annular outwardly opening casing of the annular carrier,

(b) cavity means in the annular carrier adjacent a radially inner surface thereof,

(c) aperture means in the annular carrier for providing communication between the distribution chamber means and said cavity means, and

(d) exhaust duct means for exhausting the fluid from said cavity means, said exhaust duct means comprising an opening in said turbine casing, and annular collection chamber in said turbine casing and communicating said annular collection chamber with said cavity means.

2. A turbine ring according to claim 1, further comprising:

two radial, annular, flange member which are mutually axially spaced and fixed to the inner wall of the turbine casing, the annular carrier being axially held between the flange members with an interference fit, and

means for immobilizing the annular carrier between the flange members in the circumferential direction of said annular carrier, whereby radial centering of the carrier with respect to a remainder of said turbine is maintained irrespective of expansion or contraction of said annular carrier during operation.

3. As turbine ring according to claim 2, wherein the immobilizing means comprise

pegs, and

means defining slots which receive the pegs when the annular carries is mounted between the flange members.

4. A turbine ring according to claim 1, including a plurality of axially spaced and annular recesses adjacent an interface of said annular carrier with said ceramic ring, adjacent ones of said recesses being connected by axially-extending grooves, passages formed in an axially up-stream end portion of said annular carrier for the supply of cooling fluid of said annular recesses and at least one passage in an axially down-stream end portion of said annular carrier for the exhaust of the cooling fluid from said annular recesses, the turbine ring further comprising a thin annular member positioned between said annular carrier and said ceramic ring and closing said annular recesses and axially extending grooves.

5. The turbine according to claim 1, wherein said means for applying said compression force comprise substantially axially extending mutual contact surfces of said annular carrier and said ceramic ring, said mutual contact surfaces being sized, when cold, such that said contact surface of said annular carrier has a diameter smaller than that of said ceramic ring contact surface by an amount sufficient that said annular carrier contact surface diameter is smaller than said ceramic ring contact surface diameter at all operating temperatures of said turbine.

6. The turbine according to claim 5, wherein said means for applying said compression force comprise substantially axially extending mutual contact surfaces of said annular carrier and said ceramic ring, said mutual contact surfaces being sized, when cold, such that said contact surface of said annular carrier has a diameter smaller than that of said ceramic ring contact surface by an amount sufficient that said annular carrier contact surface diameter is smaller than said ceramic ring contact surface diameter at all operating temperatures of said turbine.

7. The turbine according to claim 6, wherein said contact surface of said annular ring comprises radially inner surfaces of said projections.