Turbine shroud with forward case and full hoop blade track

Patent metadata

Field	Value
Publication number	US-10415415-B2
Application number	US-201615217305-A
Country	US
Kind code	B2
Filing date	Jul 22, 2016
Priority date	Jul 22, 2016
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.

First claim

What is claimed is:

1. A turbine shroud assembly for a gas turbine engine, the turbine shroud assembly comprising
an annular turbine case arranged around a central axis of the turbine shroud assembly,
a full hoop blade track comprising ceramic matrix composite materials located radially between the turbine case and the central axis, the blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, and
a forward case coupled to the turbine case and arranged to extend radially inwardly away from the turbine case toward the central axis and interlocked with the leading edge of the blade track to block circumferential and axial movement of the blade track relative to the turbine case while allowing radial movement of the blade track relative to the turbine case,
further comprising a carrier located radially between the turbine case and the blade track and a hollow cross-key pin that extends through the turbine case into the carrier, the carrier is arranged to define an inwardly facing thermal management chamber, and the hollow cross-key pin is configured to direct airflow through the turbine case and the carrier into the thermal management chamber toward the blade track.

2. The turbine shroud assembly of claim 1 , wherein the forward case includes an axial runner that extends from a first end to a second end axially spaced from the first end and a locator flange coupled to the axial runner toward the second end, the locator flange extends radially inwardly away from the turbine case toward the central axis, and the locator flange interlocks with the leading edge of the blade track.

3. The turbine shroud assembly of claim 2 , wherein the locator flange is formed to include a plurality of cutouts that extend radially outwardly into the locator flange, the leading edge of the blade track is formed to include a plurality of tangs that extend axially forward away from the trailing edge of the blade track toward the locator flange, and each tang is received by one of the cutouts formed in the locator flange of the forward case to interlock the forward case and the blade track.

4. The turbine shroud assembly of claim 3 , wherein the blade track includes a radial outer surface that faces the turbine case and a radial inner surface radially spaced apart from the radial outer surface and the radial outer surface of the blade track is generally cylindrical without protrusions and depressions.

5. The turbine shroud assembly of claim 3 , wherein the plurality of cutouts formed in the locator flange includes at least three cutouts and the plurality of tangs formed in the leading edge of the blade includes at least three tangs.

6. The turbine shroud assembly of claim 2 , wherein the axial runner is formed to define a plurality of apertures that extends radially through the axial runner.

7. The turbine shroud assembly of claim 1 , wherein the forward case includes a first end, a second end axially spaced apart from the first end, an axial runner that extends between the first and second ends, and a locator flange that extends radially inwardly away from the axial runner toward the central axis, the axial runner includes a band that extends between the first and second ends of the forward case, a mount flange that extends radially outwardly away from the band at the first end of the forward case, and a shoulder that extends radially outwardly away from the band at the second end of the forward case.

8. The turbine shroud assembly of claim 7 , wherein the turbine case includes a forward mount and an aft mount spaced apart axially from the forward mount, the aft mount includes a radial inner surface that faces the central axis, and the shoulder of the axial runner has an outer diameter that is larger than an inner diameter of the radial inner surface of the aft mount.

9. The turbine shroud assembly of claim 7 , wherein the shoulder is formed to include radially extending scallops arranged to allow air flow between the shoulder and the turbine case.

10. A turbine assembly for a gas turbine engine, the turbine assembly comprising
an annular turbine case arranged around a central axis of the turbine assembly,
a blade track located radially between the turbine case and the central axis, the blade track having a leading edge and a trailing edge axially spaced apart from the leading edge,
a vane assembly located radially between the turbine case and the central axis and located axially aft of the blade track, the vane assembly arranged to engage the trailing edge of the blade track to block axially aft movement of the blade track relative to the turbine case, and
a forward case coupled to the turbine case and arranged to interlock with the leading edge of the blade track to block circumferential and forward axial movement of the blade track relative to the turbine case while allowing radial movement of the blade track relative to the central axis,
wherein the forward case includes an axial runner that extends from a first end to a second end axially spaced from the first end and a locator flange coupled to the axial runner toward the second end, the locator flange extends radially inwardly away from the turbine case toward the central axis, the locator flange is formed to include a cutout that extends radially outwardly into the locator flange, the leading edge of the blade track is formed to include a tang that extends axially into the cutout to interlock the forward case and the blade track,
wherein the turbine case includes a radially inwardly extending aft mount, the axial runner includes an annular band that extends from a first end to a second end of the band, a mount flange that extends radially outwardly away from first end of the band, and a shoulder that extends radially outwardly away from the second end of the band, and the shoulder engages the aft mount of the turbine case.

11. The turbine assembly of claim 10 , wherein the axial runner includes a band and a mount flange that extends radially outwardly away from the band and the band is formed to include a plurality of radially extending apertures spaced apart from one another circumferentially about the central axis.

12. The turbine assembly of claim 10 , further comprising nozzle guide vanes located radially between the turbine case and the central axis and located axially forward of the blade track and the nozzle guide vanes engage the forward case to transmit axial loads through the forward case.

13. The turbine assembly of claim 10 , wherein the shoulder is discontinuous.

14. The turbine assembly of claim 10 , further comprising a carrier located radially between the turbine case and the blade track and a hollow cross-key pin that extends through the turbine case into the carrier, the carrier is arranged to define an inwardly facing thermal management chamber, and the hollow cross-key pin is configured to direct airflow through the turbine case and the carrier into the thermal management chamber toward the blade track.

15. A method of assembling a turbine assembly for use in a gas turbine engine, the method comprising
providing an annular turbine case arranged around a central axis of the gas turbine engine, a full hoop blade track having a leading edge and a trailing edge axially spaced apart from the leading edge, a forward case having an axially extending axial runner and a radially inwardly extending locator flange, a carrier arranged to define an inwardly facing thermal management chamber, and a hollow cross-key pin,
locating the carrier radially between the turbine case and the blade track so that the inwardly facing thermal management chamber

Assignees

• Rolls Royce Nam Tech Inc

Inventors

• Rice Edward C
• Vetters Daniel K

Classifications

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2260/36

  by a form fit connection, e.g. by interlocking · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D25/005

  Selecting particular materials · CPC title