Smart turbine shroud

• US 5,593,277 A
• Filed: 06/06/1995
• Issued: 01/14/1997
• Est. Priority Date: 06/06/1995
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Plemmons, Larry W., Di Salle, David A., Proctor, Robert, Linger, David R., Brassfield, Steven R.
• Primary Examiner(s): Lopez, F. Daniel
• Assistant Examiner(s): Lee, Michael S.
• Application Number:
  US08/467,418
• Time in Patent Office: 588 Days
• Field of Search: 415/173.1, 415/138, 415/115
• US Class Current: 415/173.1
• CPC Class Codes: F01D 11/18 using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
• CPC Class Codes: F01D 11/24 by selectively cooling-heating stator or rotor components

Abstract

A turbine shroud includes an annular outer casing having first and second radial flanges between which are suspended an adjoining annular shroud support and an annular shroud hanger. A plurality of shroud panels are joined to the shroud hanger and are positionable radially above turbine rotor blades to define a tip clearance therebetween. The four flanges are disposed in abutting contact with each other, and respective pluralities of circumferentially spaced apart first, second, and third recesses are disposed respectively between the casing first flange and the shroud flange, between the shroud flange and the hanger flange, and between the hanger flange and the casing second flange for providing radial flowpaths therebetween. The support flange and the hanger flange have respective pluralities of circumferentially spaced apart first and second metering holes extending axially therethrough for providing flow communication between the first, second, and third recesses for channeling compressor bleed air therethrough for controlling the tip clearance.

Claims

1. A turbine shroud positionable radially above a plurality of turbine rotor blades for controlling tip clearance therebetween comprising:

an annular outer casing axially split at a pair of adjacent first and second radial flanges;

an annular shroud support having a radial support flange and an integral support leg at a radially inner end thereof;

an annular shroud hanger having a radial hanger flange and integral forward and aft hanger legs at a radially inner end thereof, said shroud hanger forward leg being supported on said support shroud forward leg;

a plurality of shroud panels joined to said hanger legs and having a radially inner surface positionable radially above said rotor blades to define said tip clearance therebetween;

said support flange and said hanger flange being axially positioned between said first and second casing flanges in abutting contact with each other, and said four flanges having a plurality of bolt holes arranged on a common circumferential bolt line, each bolt hole receiving a respective bolt for axially clamping together said four flanges to support said shroud panels from said casing;

said four flanges having pluralities of circumferentially spaced apart first, second, and third recesses disposed respectively between said casing first flange and said shroud flange, between said shroud flange and said hanger flange, and between said hanger flange and said casing second flange for providing radial flowpaths therebetween; and

said support flange and said hanger flange having respective pluralities of circumferentially spaced apart first and second metering holes extending axially therethrough for providing flow communication between said first, second, and third recesses for channeling compressor bleed air therethrough for controlling said tip clearance.

2. A turbine shroud according to claim 1 wherein said first, second, and third recesses are spaced from said bolt holes.

3. A turbine shroud according to claim 2 wherein:

said support flange further includes a forward face disposed in abutting contact with an aft face of said casing first flange and includes said first recesses therein for providing a radial flowpath outwardly from above said support leg for channeling said compressor bleed air, and said first metering holes extend axially through said support flange in respective ones of said first recesses;

said hanger flange further includes a forward face disposed in abutting contact with an aft face of said support flange and includes said second recesses therein disposed in flow communication with respective ones of said first metering holes for providing a radial flowpath inwardly between said support flange and said hanger flange, and said second metering holes extend axially through said hanger flange in respective ones of said second recesses; and

said hanger flange further includes an aft face disposed in abutting contact with a forward face of said casing second flange, and includes said third recesses therein disposed in flow communication with respective ones of said second metering holes for providing a radial flowpath inwardly between said hanger flange and said casing second flange.

4. A turbine shroud according to claim 3 wherein said first and second recesses extend radially below said casing first and second flanges, respectively, for receiving said bleed air from above said shroud support forward leg and discharging said bleed air above said hanger aft leg.

5. A turbine shroud according to claim 4 further including a plurality of circumferentially spaced apart impingement holes extending radially inwardly through said hanger flange to between said hanger forward and aft legs, and disposed in flow communication with said second recesses for providing a portion of said bleed air in impingement against an outer surface of said shroud panels.

6. A turbine shroud according to claim 5 wherein said hanger forward and aft legs are spaced in part from said shroud panels to define a forward cavity thereabove, and said impingement holes are sized for maintaining a positive pressure backflow margin therein.

7. A turbine shroud according to claim 6 further including:

an annular recessed manifold extending circumferentially around said hanger flange radially below said forward face thereof, and below said second recesses in flow communication therewith for receiving and circumferentially spreading said bleed air therein; and

said impingement holes are disposed in flow communication with said manifold.

8. A turbine shroud according to claim 7 wherein respective ones of said first, second, and third recesses are axially aligned together, and said first and second metering holes are radially offset from each other for dividing flow of said bleed air between said second and third recesses.

9. A turbine shroud according to claim 7 wherein said first and second metering holes have different diameters for selectively dividing flow of said bleed air between said second and third recesses.

10. A turbine shroud according to claim 7 wherein said first and third recesses are circular, and said second recesses are generally U-shaped.