# US 2025/0146418 A1 · Turbine incorporating splitters

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 2025/0146418 A1
- Document ID: US20250146418A1
- Status: Published application
- Kind: A1
- Application number: 19/013,045
- Filed: 2025-01-08
- Published: 2025-05-08
- Earliest claimed: 2017-03-09
- Assignees: General Electric Company; GE Avio S.r.l.
- Applicants: General Electric Company; GE Avio S.r.l.
- Inventors: Jeffrey Donald Clements; Paul Hadley Vitt; Francesco Bertini; Aspi Rustom Wadia; Ganesh Seshadri; Mahendran Manoharan; Ravikanth Avancha
- Web page: https://patentgrep.com/patent/US20250146418A1

## CPC

- F01D 5/145: {Means for influencing boundary layers or secondary circulations (for compressors F04D29/68)}
- F01D 5/146: {of blades with tandem configuration, split blades or slotted blades}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/284: {Selection of ceramic materials}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F04D 29/324: {Blades}
- F05D 2240/12: Fluid guiding means, e.g. vanes
- 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)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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 turbomachinery apparatus 10 includes: a turbine 22, including: a turbine component 36 defining at least one arcuate flowpath surface 40; an array of axial-flow turbine airfoils 46 extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils 146 extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.

## Claims

### Claim 1

A turbomachinery apparatus, comprising:
a turbine, comprising:
a turbine component defining an arcuate flowpath surface;
an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and
a plurality of splitter airfoils extending from the flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio less than a thickness ratio of the turbine airfoils.

### Claim 2 (depends on 1)

The apparatus of claim 1, wherein the turbine airfoils comprise a metallic alloy and the splitter airfoils comprise a nonmetallic high-temperature capable material.

### Claim 3 (depends on 1)

The apparatus of claim 1, wherein the splitter airfoils comprise a ceramic matrix composite material.

### Claim 4 (depends on 1)

The apparatus of claim 1, wherein the thickness ratio of the splitter airfoils is less than approximately 5%.

### Claim 5 (depends on 1)

The apparatus of claim 1, wherein the thickness ratio of the splitter airfoils is approximately 2%.

### Claim 6 (depends on 1)

The apparatus of claim 1, wherein at least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the turbine airfoils.

### Claim 7 (depends on 6)

The apparatus of claim 6, wherein the span dimension of the splitter airfoils is 50% or less of the span dimension of the turbine airfoils.

### Claim 8 (depends on 6)

The apparatus of claim 6, wherein the chord dimension of the splitter airfoils adjacent the flowpath surface is 50% or less of the chord dimension of the turbine airfoils adjacent the flowpath surface.

### Claim 9 (depends on 1)

The apparatus of claim 1, further comprising:
a combustor disposed upstream of the turbine, in fluid flow communication with the turbine;
a compressor disposed upstream of the combustor, in fluid flow communication with the combustor; and
wherein the turbine is connected in mechanical driving relationship with the compressor.

### Claim 10

A turbine apparatus, comprising:
a turbine rotor stage including a disk rotatable about a centerline axis, the disk defining a rotor flowpath surface, and an array of axial-flow turbine blades extending outward from the rotor flowpath surface, the turbine blades defining spaces therebetween;
a turbine nozzle stage comprising at least one wall defining a stator flowpath surface, and an array of axial-flow turbine vanes extending away from the stator flowpath surface, the turbine vanes defining spaces therebetween; and
wherein at least one of the rotor or nozzle stages includes an array of splitter airfoils extending from at least one of the flowpath surfaces thereof, the splitter airfoils disposed in the spaces between the turbine blades or turbine vanes of the corresponding stage, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the corresponding turbine blades or turbine vanes.

### Claim 11 (depends on 10)

The apparatus of claim 10, wherein the turbine blades and vane comprise a metallic alloy and the splitter airfoils comprise a nonmetallic high-temperature capable material.

### Claim 12 (depends on 10)

The apparatus of claim 10, wherein the splitter airfoils comprise a ceramic matrix composite material.

### Claim 13 (depends on 10)

The apparatus of claim 10, wherein the splitter airfoils have a thickness ratio of less than approximately 5%.

### Claim 14 (depends on 10)

The apparatus of claim 10, wherein the thickness ratio of the splitter airfoils is less than a thickness ratio of approximately 2%.

### Claim 15 (depends on 10)

The apparatus of claim 10, wherein at least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the of the turbine blades or turbine vanes, respectively.

### Claim 16 (depends on 10)

The apparatus of claim 10, wherein the span dimension of the splitter airfoils is 50% or less of the span dimension of the corresponding turbine blades or turbine vanes.

### Claim 17 (depends on 15)

The apparatus of claim 15, wherein the chord dimension of the splitter airfoils adjacent the flowpath surface is 50% or less of the chord dimension of the corresponding rotor or stator airfoils adjacent the corresponding flowpath surface.

### Claim 18 (depends on 10)

The apparatus of claim 10, wherein the at least one wall of the nozzle stage faces radially outward relative to the centerline axis and the splitter airfoils extend radially outward from the at least one wall.

### Claim 19 (depends on 10)

The apparatus of claim 10, wherein the at least one wall of the nozzle stage faces radially inward relative to the centerline axis and the splitter airfoils extend radially inward from the at least one wall.

### Claim 20 (depends on 10)

The apparatus of claim 10, wherein at least one of the spaces has two or more of the splitter airfoils positioned therein.