# US 2019/0376392 A1 · Gas turbine

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- Number: US 2019/0376392 A1
- Document ID: US20190376392A1
- Status: Published application
- Kind: A1
- Application number: 16/462,466
- Filed: 2017-12-01
- Published: 2019-12-12
- Earliest claimed: 2016-12-01
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Rolls-Royce Deutschland Ltd & Co KG
- Inventors: Karl SCHREIBER
- Web page: https://patentgrep.com/patent/US20190376392A1

## CPC

- F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)}
- F01D 5/284: {Selection of ceramic materials}
- F01D 5/3007: {of axial insertion type}
- F01D 5/3084: {the blades being made of ceramics}
- F01D 5/323: {Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor}
- F05D 2300/6033: Ceramic matrix composites [CMC]
- 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

A gas turbine having at least one disk, wherein turbine blade elements are connected via connection means to the at least one disk, wherein the connection means are arranged in the interior of the turbine blade elements in a region radially above the disk in the radial direction of the turbine blade elements, in particular in a region which is in the driving airflow during the operation of the gas turbine, and the turbine blade elements have at least two zones composed of different materials, wherein the at least two zones adjoin one another in particular in the radial direction, and in that a zone with a material suited to compressive stress, in particular a ceramic, in particular an yttrium-stabilized zirconium oxide, is arranged radially below the connection means, and a zone with a material suited to tensile stress, in particular CMSX 4, is arranged radially above the connection means.

## Claims

### Claim 1

A gas turbine having at least one disk, wherein turbine blade elements are connected via connection means to the at least one disk, wherein
the connection means are arranged in the interior of the turbine blade elements in a region radially above the disk in the radial direction of the turbine blade elements, in particular in a region which is in the driving airflow during the operation of the gas turbine, and
the turbine blade elements have at least two zones composed of different materials, wherein the at least two zones adjoin one another in particular in the radial direction, and
in that a zone with a material suited to compressive stress, in particular a ceramic, in particular an yttrium-stabilized zirconium oxide, is arranged radially below the connection means, and a zone with a material suited to tensile stress, in particular CMSX 4, is arranged radially above the connection means.

### Claim 2 (depends on 1)

The gas turbine as claimed in claim 1, wherein the connection means are arranged radially on the inside, radially in the center or radially on the outside in the region radially above the disk, in particular in the region of the turbine blade elements which is in the driving airflow during the operation of the gas turbine.

### Claim 3 (depends on 1)

The gas turbine as claimed in claim 1, wherein the connection means are designed for positive joining, nonpositive joining and/or material joining.

### Claim 4 (depends on 3)

The gas turbine as claimed in claim 3, wherein the positive connection means have positive joining means, in particular shoulders, projections and/or undercuts for the axial and/or radial fixing of the turbine blade elements.

### Claim 5 (depends on 3)

The gas turbine as claimed in claim 3, wherein, in the case of nonpositive connection means, frictional joining can be achieved by means of a wedge connection, in particular in the disk, and/or by means of shrink-fit connections.

### Claim 6 (depends on 3)

The gas turbine as claimed in claim 3, wherein, in the case of material connection means, there is a laser-welded joint between the turbine blade elements and the disk.

### Claim 7 (depends on 1)

The gas turbine as claimed in claim 1, wherein at least one parting line is arranged between two zones of different material in the turbine blade elements radially below the connection means.

### Claim 8 (depends on 1)

The gas turbine as claimed in claim 1, characterized by wedge elements for clamping the disk to the turbine blade elements and/or for producing positive joining between the disk and the turbine blade elements.

### Claim 9 (depends on 1)

The gas turbine as claimed in claim 1, wherein the turbine blade elements are connected radially on the outside via a welded joint to the at least one disk.

### Claim 10 (depends on 1)

The gas turbine as claimed in claim 1, wherein the turbine blade elements can be assembled from at least two parts.

### Claim 11 (depends on 1)

The gas turbine as claimed in claim 1, wherein it is designed as an aircraft engine, as a vehicle propulsion system, as a ship's propulsion system or as a stationary gas turbine.

### Claim 12 (depends on 1)

A turbine blade element or disk, in particular configured and designed for use in a gas turbine as claimed in claim 1.