Turbine clearance control utilizing low alpha material

Patent metadata

Field	Value
Publication number	US-2016153286-A1
Application number	US-201414905351-A
Country	US
Kind code	A1
Filing date	Jul 2, 2014
Priority date	Jul 15, 2013
Publication date	Jun 2, 2016
Grant date	—

Abstract

A turbine module comprises a stator assembly disposed annularly about a rotor assembly. The rotor assembly includes a plurality of turbine blades circumferentially distributed about a turbine disk. The stator assembly includes at least one case segment and an abradable surface disposed radially adjacent to a tip of each of the plurality of rotor blades. The turbine blades each include an airfoil section with a first gamma-phase titanium aluminide (gamma-TiAl) substrate, and the at least one case segment has a second gamma-TiAl substrate.

First claim

1 . A turbine module comprising:
a rotor assembly including a plurality of turbine blades circumferentially distributed about a turbine disk, the plurality of turbine blades each including an airfoil section with a first gamma-phase titanium aluminide (gamma-TiAl) substrate; and a stator assembly disposed annularly about the rotor assembly, the stator assembly including an abradable surface disposed radially adjacent to a tip of each of the plurality of rotor blades, the stator assembly including at least one case segment with a second gamma-TiAl substrate.

2 . The turbine module of claim 1 , wherein the first gamma-TiAl substrate includes a first composition and the second gamma-TiAl substrate includes a second composition.

3 . The turbine module of claim 2 , wherein at least one of the first composition and the second composition includes less than about 15 vol % alpha-TiAl.

4 . The turbine module of claim 2 , wherein at least one of the first composition and the second composition includes less than about 5 vol % alpha-TiAl.

5 . The turbine module of claim 2 , wherein the second composition is substantially different from the first composition.

6 . The turbine module of claim 2 , wherein the second composition is substantially identical to the first composition.

7 . The turbine module of claim 1 , wherein the turbine disk includes a gamma-TiAl substrate with a third composition.

8 . The turbine module of claim 1 , wherein the third composition is substantially identical to the first composition.

9 . The turbine module of claim 8 , wherein the plurality of turbine blades are joined to the turbine disk to form an integrally bladed rotor (IBR).

10 . The turbine module of claim 1 , wherein the stator assembly further comprises:
a plurality of turbine vanes circumferentially distributed about the at least one case segment, each vane including an airfoil section with a fourth gamma-phase titanium aluminide (gamma-TiAl) substrate

11 . A gas turbine engine comprising:
a compressor section including a compressor module adapted to compress a working fluid; a combustor section adapted to mix fuel with the working fluid compressed by the compressor module and discharge resulting combustion products; and a turbine section including a turbine module adapted to receive combustion products from the combustor, the turbine module including a stator assembly disposed annularly about a rotor assembly, the rotor assembly having a plurality of gamma-phase titanium aluminide (gamma-TiAl) turbine blades circumferentially distributed about a turbine disk, and the stator assembly having a gamma-TiAl case disposed annularly about the rotor assembly with an abradable surface of the gamma-TiAl case disposed radially adjacent to a tip of each rotor blade.

12 . The engine of claim 11 , wherein the gamma-TiAl turbine blades each include a first composition and the gamma-TiAl case includes a second composition.

13 . The engine of claim 12 , wherein at least one of the first composition and the second composition includes less than about 15 vol % alpha-TiAl.

14 . The engine of claim 12 , wherein at least one of the first composition and the second composition includes less than about 5 vol % alpha-TiAl.

15 . The engine of claim 12 , wherein the second composition is substantially different from the first composition.

16 . The engine of claim 12 , wherein the second composition is substantially identical to the first composition.

17 . The engine of claim 11 , wherein the turbine disk comprises gamma-TiAl with a third composition.

18 . The engine of claim 11 , wherein the third composition is substantially identical to the first composition.

19 . The engine of claim 18 , wherein the plurality of turbine blades are joined to the turbine disk to form an integrally bladed rotor (IBR).

20 . The engine of claim 11 , wherein the at least one casing segment is isolated from an engine bleed air system.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Alvanos Ioannis

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D5/28 Primary

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F05D2300/174

  Titanium alloys, e.g. TiAl · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F01D5/34

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title