# US 10,502,084 B2 · Module for a gas turbine

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- Number: US 10,502,084 B2
- Document ID: US10502084B2
- Status: Granted
- Kind: B2
- Application number: 15/296,305
- Filed: 2016-10-18
- Published: 2017-04-20
- Granted: 2019-12-10
- Earliest claimed: 2015-10-20
- Assignees: MTU Aero Engines AG
- Applicants: MTU Aero Engines AG
- Inventors: Werner Humhauser; Hermann Klingels; Rudolf Stanka; Alois Eichinger
- Web page: https://patentgrep.com/patent/US10502084B2

## CPC

- F01D 11/18: using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
- F01D 5/28: Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion
- F01D 25/005: {Selecting particular materials}
- F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045})
- F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing
- F01D 25/30: Exhaust heads, chambers, or the like
- F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)}
- F01D 25/162: {Bearing supports}
- F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)}
- F01D 25/246: {Fastening of diaphragms or stator-rings}
- F05D 2220/32: in gas turbines
- F05D 2300/5021: Expansivity
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

## Claims

### Claim 1

A module for a gas turbine, wherein the module comprises:
a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient,
a rotationally symmetrical component for guiding hot gas of a second material having a second linear thermal expansion coefficient which is lower than the first linear thermal expansion coefficient,
at least one annular structure, which is arranged radially within the rotationally symmetrical component,
at least three struts, each having a radially inner end and a radially outer end, the outer ends being secured on the outer casing and the inner ends being secured on the annular structure,
wherein the rotationally symmetrical component comprises at least one first fixing, the fixing being free in radial direction and fixed in axial direction and being arranged between the rotationally symmetrical component and the outer casing and/or between the rotationally symmetrical component and the annular structure, and wherein the module further comprises at least three second fixings, which have an elastic effect in at least one of a radial direction, an axial direction and a circumferential direction, the second fixing being arranged between the rotationally symmetrical component and at least one strut of the at least three struts and/or between the rotationally symmetrical component and the annular structure.

### Claim 2 (depends on 1)

The module of claim 1, wherein the first material comprises a metal alloy resistant to high temperatures.

### Claim 3 (depends on 1)

The module of claim 1, wherein the second material comprises a fiber-reinforced ceramic.

### Claim 4 (depends on 1)

The module of claim 1, wherein the first material has a linear thermal expansion coefficient of from 10 to 20 μm/m/K.

### Claim 5 (depends on 1)

The module of claim 1, wherein second material has a linear thermal expansion coefficient of from 1 to 5 μm/m/K.

### Claim 6 (depends on 1)

The module of claim 1, wherein the rotationally symmetrical component comprises a radially outer wall and a radially inner wall which are connected to one another via at least three radially extending and hollow fairings.

### Claim 7 (depends on 6)

The module of claim 6, wherein the outer wall has a first opening at a level of a fairing and/or the inner wall has a second opening at a level of a fairing.

### Claim 8 (depends on 7)

The module as claimed in claim 7, wherein at least one strut of the at least three struts passes through the radially outer wall and the radially inner wall.

### Claim 9 (depends on 6)

The module of claim 6, wherein a substantially axially extending arm is formed integrally on at least one of the at least three struts, a free end of the arm being arranged in a receptacle which is formed in a cavity of a fairing.

### Claim 10 (depends on 9)

The module of claim 9, wherein a metal plate or sheet is arranged between a wall of the receptacle and the free end.

### Claim 11 (depends on 1)

The module of claim 1, wherein the module further comprises an inner ring, one end of the inner ring being secured on the annular structure, and a fixing receptacle being formed integrally on an inner wall.

### Claim 12 (depends on 11)

The module of claim 11, wherein the module further comprises at least one radially or axially extending rod, one end of the rod being arranged in a fixing receptacle in such a way as to be movable in axial direction of the rod and the other end of the rod being connected to the other end of the inner ring.

### Claim 13 (depends on 11)

The module as claimed in claim 11, wherein a cylindrical cage which is secured on the fixing receptacle is formed integrally on the other end of the inner ring.

### Claim 14 (depends on 13)

The module as claimed in claim 13, wherein a wall of the cylindrical cage comprises at least one aperture.

### Claim 15 (depends on 1)

The module of claim 1, wherein the first fixing is arranged in a vicinity of an upstream edge of the rotationally symmetrical component.

### Claim 16 (depends on 1)

The module of claim 1, wherein the first fixing is arranged at the same axial level as the second fixing.

### Claim 17 (depends on 1)

The module of claim 1, wherein the module is an intermediate casing of a turbine.