# US 7,607,286 B2 · Regenerative turbine blade and vane cooling for a tip turbine engine

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- Number: US 7,607,286 B2
- Document ID: US7607286B2
- Status: Granted
- Kind: B2
- Application number: 11/719,956
- Filed: 2004-12-01
- Published: 2007-12-27
- Granted: 2009-10-27
- Earliest claimed: 2004-12-01
- Assignees: United Technologies Corporation
- Inventors: Gabriel L. Suciu; James W. Norris; Craig A. Nordeen
- Web page: https://patentgrep.com/patent/US7607286B2

## CPC

- F02C 3/073: the compressor and turbine stages being concentric
- F01D 5/022: {with concentric rows of axial blades}
- F01D 5/187: {Convection cooling}
- F02K 3/068: being characterised by a short axial length relative to the diameter
- F05D 2260/205: Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- 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 fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.

## Claims

### Claim 1

A method of regenerative cooling of a tip turbine engine comprising:
locating a turbine blade that extends from a fan blade downstream of a discharge flow from an annular combustor;
locating a turbine stator downstream of a discharge flow from the annular combustor;
communicating a regenerative cooling airflow through a turbine stator passage in the turbine stator; and
communicating the regenerative cooling airflow from the turbine stator passage into the annular combustor through a static structure flow passage subsequent to communicating the regenerative cooling airflow the turbine stator passage, the static structure flow passage having an axial component generally parallel to an axis of rotation of the fan blade.

### Claim 2

A tip turbine engine comprising:
a compressor for compressing a core airflow;
a fan for accelerating bypass airflow and having a core airflow passage that receives said core airflow from said compressor;
an annular combustor for introducing fuel and combusting said core airflow from said fan; and
a turbine for extracting energy from said core airflow exiting said annular combustor, said turbine having at least one stage defined by a turbine blade that extends from a fan blade and a turbine vane, wherein said vane has a vane passage to receive a regenerative cooling airflow portion of said core airflow from said fan, said regenerative cooling portion of said core airflow exiting said vane passage for communication to said annular combustor, said regenerative cooling airflow portion of said core airflow is communicated through a turbine blade passage of said turbine blade prior to communication through said turbine vane passage.

### Claim 3 (depends on 2)

The tip turbine engine as recited in claim 2, wherein a static structure flow passage communicates the regenerative cooling airflow within said static structure flow passage in a direction generally opposite a bypass airflow generated by said fan blade section.

### Claim 4 (depends on 1)

A method as recited in claim 1, wherein communicating the regenerative cooling airflow from the turbine stator passage into the annular combustor in a direction generally opposite a propulsive airflow generated by the fan blade.