# US 11,028,698 B1 · Ceramic radial turbine

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- Number: US 11,028,698 B1
- Document ID: US11028698B1
- Status: Granted
- Kind: B1
- Application number: 16/446,970
- Filed: 2019-06-20
- Granted: 2021-06-08
- Earliest claimed: 2018-06-22
- Assignees: Florida Turbine Technologies, Inc.
- Applicants: Florida Turbine Technologies, Inc.
- Inventors: Russell B Jones; Edwin L Kite
- Web page: https://patentgrep.com/patent/US11028698B1

## CPC

- F01D 5/025: {Fixing blade carrying members on shafts (attachment of a member on a shaft in general F16D1/06; for non-positive displacement pumps F04D29/00)}
- F01D 5/04: for radial-flow machines or engines
- F01D 5/046: {Heating, heat insulation or cooling means}
- F01D 5/048: {Form or construction}
- F01D 5/085: {cooling fluid circulating inside the rotor}
- F01D 5/284: {Selection of ceramic materials}
- F01D 25/005: {Selecting particular materials}
- F01D 25/12: Cooling
- F04D 17/10: for compressing or evacuating
- F04D 29/0513: {hydrostatic; hydrodynamic thrust bearings}
- F04D 29/266: {mounting compressor rotors on shafts}
- F04D 29/284: {for compressors}
- F05D 2220/32: in gas turbines
- F05D 2220/40: in turbochargers
- F05D 2240/24: for turbines
- F05D 2260/20: Heat transfer, e.g. cooling
- F05D 2260/31: Retaining bolts or nuts
- F05D 2300/20: Oxide or non-oxide ceramics
- 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

## Abstract

A small gas turbine engine with a ceramic turbine to allow for higher turbine inlet temperatures, where a metallic compressor is secured to a ceramic shaft extending from a ceramic turbine to form a single piece ceramic shaft and turbine, where a threaded nut secures a split ring retainer on the compressor end of the ceramic shaft. A hollow thrust runner is compressed between the compressor disk and the turbine disk by the threaded nut to secure rotor together. A centering spring forms a tight fit between the metallic thrust runner and the ceramic shaft on the turbine side.

## Claims

### Claim 1

A rotor for a small gas turbine engine comprising:
a metallic compressor;
a ceramic turbine with a ceramic shaft forming a single piece ceramic shaft and ceramic turbine;
a metallic thrust runner secured between the metallic compressor and the ceramic turbine with the ceramic shaft extending within the metallic thrust runner and forming a cooling air passage;
a split ring retainer and a threaded nut secured over the ceramic shaft to secure the metallic compressor to the ceramic shaft; and
a centering spring secured between an inner surface of the metallic thrust runner and an outer surface of the ceramic shaft near to the ceramic turbine, the centering spring includes a plurality of radial outward projections and a plurality of radial inward projections offset to produce a spring effect between the metallic thrust runner and the ceramic shaft.

### Claim 2 (depends on 1)

The rotor for the small gas turbine engine of claim 1, wherein the ceramic shaft on the compressor end has a recess on an outer surface; and
the split ring retainer has an inner projecting piece that fits within the recess of the ceramic shaft.

### Claim 3 (depends on 1)

The rotor for the small gas turbine engine of claim 1, wherein the split ring retainer includes threads on an outer surface; and
the retainer nut includes threads on an inner surface to engage the threads on the split ring retainer.

### Claim 4 (depends on 1)

The rotor for the small gas turbine engine of claim 1, wherein the metallic thrust runner includes an annular thrust bearing disk extending outward.

### Claim 5 (depends on 1)

The rotor for the small gas turbine engine of claim 1, wherein the threaded nut retains the split ring retainer in place on the ceramic shaft and applies axial force to the compressor to compress the metallic thrust runner between the compressor and the turbine.

### Claim 6

A rotor for a small gas turbine engine comprising:
a metallic compressor;
a ceramic turbine with a ceramic shaft forming a single piece ceramic shaft and ceramic turbine;
a metallic thrust runner secured between the metallic compressor and the ceramic turbine with the ceramic shaft extending within the metallic thrust runner and forming a cooling air passage;
a split ring retainer and a threaded nut secured over the ceramic shaft to secure the metallic compressor to the ceramic shaft; and
a plurality of torque keys between an inner surface of a compressor disk of the metallic compressor and an outer surface of the ceramic shaft provide a torque transfer from the ceramic shaft to the compressor disk.