Temperature control device for gas turbines

• US 4,329,113 A
• Filed: 10/05/1979
• Issued: 05/11/1982
• Est. Priority Date: 10/06/1978
• Status: Expired due to Term

• Current Assignee: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA (Safran SA)
• Original Assignee: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA (Safran SA)
• Inventors: Glowacki, Pierre A., Mandet, Gerard M. F., Ayache, Michel R.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US06/082,338
• Time in Patent Office: 949 Days
• Field of Search: 415/116-117, 415/174, 415/175
• US Class Current: 415/116
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Abstract

A portion of the stator of a gas turbine known as turbine shroud, which isituated radially opposite the mobile vanes of a turbine stage includes an "abradable" member supported by a first shell braced by a second shell and connected with turbine casing 2 by a thin, i.e. flexible, annular wall member embedded in a casing. Cooling air inflates the second shell so as to brace the exterior shell and circulates between the two shells so as to cool them and also cools the "abradable" member by impingement. The present invention is applicable to aviation turbojets.

Claims

1. A gas turbine shroud including a casing and an abradable member mounted on an annular support, said support comprising:

a first annular shell having an interior wall portion;

a flexible annular wall interconnecting said first shell to said turbine casing;

a second shell mounted inside said first shell for bracing said first shell and for receiving compressed air so as to brace said first shell; and

means for circulating air between said first and second shells so as to cool said first and second shells and for circulating air along said interior wall portion of said first shell onto said abradable member so as to cool said abradable member by impingement with air.

2. A turbine shroud as set forth in claim 1 operatively connected to a combustion chamber;

wherein said means for circulating air further comprises a combustion chamber casing and wherein said second shell further comprises a perforated section to which the air is circulated such that two air currents are formed at the level of said perforated section so as to circulate between said first and second shell and to trap dust.

3. A turbine shroud as set forth in claim 2, said flexible wall further comprising first and second parts secured end-to-end, said first part being integral with said first shell wherein said second shell further comprises a material having a low coefficient of thermal expansion, said second part being connected to said turbine casing and comprising the same material as said casing.

4. A turbine shroud as set forth in claim 3 further comprising means for connecting said second part of said flexible wall to said turbine casing and wherein said first and second parts of said flexible wall are secured together at a point approximately midway between said means for connecting said second part of said flexible wall to said turbine casing and said first shell such that bending stresses at said midway point are nearly zero.

5. A turbine shroud as set forth in claim 4, said second shell comprising first and second parts integrally secured, said first and second parts of said first and second shells respectively forming a passage for circulation of air to said abrading member and further comprising a turbine distributor wherein said second part of said second shell contacts said turbine distributor and comprises the same material as said casing.

6. A turbine shroud as set forth in claim 2, wherein said air further comprises air circulating from said combustion chamber and communicating with an exterior wall of said flexible wall, with an exterior face of an outside wall of said first shell and with a downstream face of a downstream wall of said first shell such that said air is expelled into a turbine jet, said second shell including passages radially crossing said outside wall and communicating with cool secondary air flowing around said casing, and said secondary air inflating said second shell and escaping through apertures formed in said second shell so as to form a stream of air which circulates between said first and second shells.

7. A turbine shroud as set forth in claim 6, further comprising a sheet metal sleeve member disposed between said first and second shells having a plurality of apertures formed therein.