Shroud assembly for gas turbine engine

• US 10,301,960 B2
• Filed: 07/13/2015
• Issued: 05/28/2019
• Est. Priority Date: 07/13/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Stapleton, David Scott, Heitman, Bryce Loring, Armanios, Laura Isabelle
• Primary Examiner(s): Shanske, Jason
• Assistant Examiner(s): Haghighian, Behnoush
• Application Number:
  US14/797,240
• Publication Number:
  US 20170016341A1
• Time in Patent Office: 1,415 Days
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• 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 25/005 Selecting particular materials
• CPC Class Codes: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/128 Nozzles
• CPC Class Codes: F05D 2240/35 Combustors or associated equipment
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: F05D 2260/31 Retaining bolts or nuts
• CPC Class Codes: F05D 2300/10 Metals, alloys or intermetallic compounds
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.

Claims

1. A shroud assembly for a gas turbine engine, the shroud assembly comprising:

a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm;

a shroud, the shroud comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface, the shroud connected to the hanger;

a support member positioned axially forward of the forward hanger arm, the support member comprising a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud; and

a hanger plate disposed between and in contact with the radially outer portion and the forward hanger arm.

2. The shroud assembly of claim 1, wherein the radially outer portion contacts the forward hanger arm.

3. The shroud assembly of claim 1, wherein the hanger plate comprises a radially outer portion connected between the radially outer portion of the support member and the forward hanger arm and a radially inner portion disposed in the gap, and wherein a secondary gap is defined between the radially inner portion of the support member and the radially inner portion of the hanger plate.

4. The shroud assembly of claim 1, wherein the support member further comprises a forward surface and an aft surface axially spaced from the forward surface, and wherein the support member further comprises a protrusion extending axially from the forward surface between the radially outer portion and radially inner portion.

5. The shroud assembly of claim 1, wherein the hanger further comprises a forward flange and a rear flange each extending from the hanger body, and wherein the shroud further comprises a forward flange and a rear flange each extending from the outer surface of the shroud body, the rear flange of the shroud axially spaced from the forward flange of the shroud, and wherein the forward flange and rear flange of the shroud are connected to the forward flange and the rear flange of the hanger to connect the shroud to the hanger.

6. The shroud assembly of claim 1, wherein the shroud is formed from a ceramic matrix composite.

7. The shroud assembly of claim 1, wherein the hanger is formed from a metal.

8. A shroud assembly for a gas turbine engine, the shroud assembly comprising:

a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm;

a shroud, the shroud comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface, the shroud connected to the hanger;

a support member positioned axially forward of the forward hanger arm, the support member comprising a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud; and

a mechanical fastener connecting the radially outer portion and the forward hanger arm.

9. The shroud assembly of claim 8, wherein the mechanical fastener comprises a nut and a bolt.

10. A shroud assembly for a gas turbine engine, the shroud assembly comprising:

a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm;

a shroud, the shroud comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface, the shroud connected to the hanger; and

a support member positioned axially forward of the forward hanger arm, the support member comprising a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud, wherein the support member is formed from a metal.

11. A turbine section of a gas turbine engine, comprising:

a shroud assembly, the shroud assembly comprising;

a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm;

a shroud, the shroud comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface, the shroud connected to the hanger; and

a support member positioned axially forward of the forward hanger arm, the support member comprising a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud, wherein the support member further comprises a forward surface and an aft surface axially spaced from the forward surface, and wherein the support member further comprises a protrusion extending axially from the forward surface between the radially outer portion and radially inner portion; and

a nozzle assembly positioned axially forward of the shroud assembly, the nozzle assembly comprising;

an airfoil; and

an outer band positioned radially outward of the airfoil, the outer band comprising a rear surface, the rear surface in contact with the radially inner portion of the support member of the shroud assembly.

12. The turbine section of claim 11, wherein the radially outer portion contacts the forward hanger arm.

13. The turbine section of claim 11, further comprising a hanger plate disposed between and in contact with the radially outer portion and the forward hanger arm.

14. The turbine section of claim 11, further comprising a mechanical fastener connecting the radially outer portion and the forward hanger arm.

15. The turbine section of claim 11, wherein the shroud is formed from a ceramic matrix composite.

16. The turbine section of claim 11, wherein the hanger is formed from a metal.

17. The turbine section of claim 11, wherein the support member is formed from a metal.

18. A gas turbine engine, comprising:

a compressor section;

a combustion section;

a turbine section; and

a shroud assembly disposed in one of the compressor or the turbine, the shroud assembly comprising;

a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm;

a shroud, the shroud comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface, the shroud connected to the hanger;

a support member positioned axially forward of the forward hanger arm, the support member comprising a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud; and

a hanger plate disposed between and in contact with the radially outer portion and the forward hanger arm.