# US 10,502,095 B2 · Internally cooled spoke

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

- Number: US 10,502,095 B2
- Document ID: US10502095B2
- Status: Granted
- Kind: B2
- Application number: 15/340,353
- Filed: 2016-11-01
- Published: 2017-02-16
- Granted: 2019-12-10
- Earliest claimed: 2012-01-30
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Paul K. Sanchez; Kalpendu J. Parekh; William A. Daniels; John S. Tu
- Web page: https://patentgrep.com/patent/US10502095B2

## CPC

- F01D 25/14: Casings modified therefor (double casings F01D25/26)
- F01D 25/12: Cooling
- F01D 25/162: {Bearing supports}
- 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})
- F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P)
- F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep
- F02K 3/04: the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F01D 25/16: Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C)
- F01D 25/246: {Fastening of diaphragms or stator-rings}
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2260/20: Heat transfer, e.g. cooling
- 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)
- 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)
- 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 turbine engine includes a compressor section, a combustor section in fluid communication with the compressor section, a high pressure turbine in fluid communication with the combustor, a low pressure turbine in fluid communication with the high pressure turbine, and a mid-turbine frame located axially between the high pressure turbine and the low pressure turbine. The mid-turbine frame includes an outer frame case, an inner frame case, and a plurality of hollow spokes that distribute loads from the inner frame case to the outer frame case. The spokes are hollow to allow cooling airflow to be supplied through the spokes to the inner frame case.

## Claims

### Claim 1

A turbine engine comprising:
a combustor;
a first spool comprising a high pressure compressor connected to a high pressure turbine;
a second spool comprising a low pressure compressor connected to a low pressure turbine; and
a mid-turbine frame located axially between the high pressure turbine and the low pressure turbine, the mid-turbine frame having an outer frame case connected to an inner frame case via a plurality of cooled spokes, wherein each of the plurality of cooled spokes has a radially outer end and a radially inner end and is hollow within a spoke wall for supplying cooling airflow from outside the outer frame case to the inner frame case, wherein the inner frame case includes a manifold defined by an outer diameter annular portion, an inner diameter annular portion, first and second radial portions of the inner frame case that extend radially between the outer diameter annular portion and the inner diameter annular portion, and wherein a radially inner end of the spoke wall of each of the plurality of cooled spokes meets the outer diameter annular portion of the manifold at an opening in the outer diameter annular portion extending from a radially outer surface of the outer diameter annular portion and a radially inner surface of the outer diameter annular portion, and terminates between the radially outer surface of the outer diameter annular portion and the radially inner surface of the outer diameter annular portion to define an airflow path from each of the plurality of cooled spokes into the manifold that allows the manifold to receive and combine the cooling airflow from the plurality of cooled spokes.

### Claim 2 (depends on 1)

The turbine engine of claim 1, wherein the mid-turbine frame includes three or more of the plurality of cooled spokes evenly distributed around the inner frame case.

### Claim 3 (depends on 1)

The turbine engine of claim 1, wherein the outer frame case includes a plurality of bosses located on an outer surface of the outer frame case for attachment to each of the plurality of cooled spokes.

### Claim 4 (depends on 1)

The turbine engine of claim 1, wherein the second spool further comprises:
a gearbox connected to at least one of the low pressure compressor and low pressure turbine; and
a fan connected to the gearbox.

### Claim 5

A mid-turbine frame located in a gas turbine engine axially aft of a high pressure turbine and fore of a low pressure turbine, the mid-turbine frame comprising:
an outer frame case;
an inner frame case; and
a plurality of hollow spokes each having a spoke wall with a radially outer end and a radially inner end, the spoke wall being attached between the outer frame case and the inner frame case to distribute force from the inner frame case to the outer frame case, wherein each of the plurality of hollow spokes is configured to receive a cooling airflow therethrough;
wherein the inner frame case includes a manifold defined by an outer diameter annular wall, an inner diameter annular wall, and first and second axial walls of the inner frame case that extend radially between the outer diameter annular wall and the inner diameter annular wall; and
wherein a radially inner end of the spoke wall of each of the plurality of hollow spokes meets the outer diameter annular wall of the manifold at an opening in the outer diameter annular wall of the manifold and terminates radially between a radially outer surface of the outer diameter annular wall and a radially inner surface of the outer diameter annular wall to define an airflow path from each of the plurality of hollow spokes into the manifold that allows the manifold to receive and combine the cooling airflow provided via the plurality of hollow spokes.

### Claim 6 (depends on 5)

The mid-turbine frame of claim 5, wherein the mid-turbine frame includes three or more of the plurality of hollow spokes evenly distributed around the inner frame case.

### Claim 7 (depends on 5)

The mid-turbine frame of claim 5, wherein the outer frame case includes a plurality of bosses located on an outer surface of the outer frame case for attachment to each of the plurality of hollow spokes.

### Claim 8 (depends on 5)

The mid-turbine frame of claim 5, wherein the high pressure turbine is connected to a high pressure compressor.

### Claim 9 (depends on 5)

The mid-turbine frame of claim 5, wherein the low pressure turbine is connected to a low pressure compressor.

### Claim 10 (depends on 9)

The mid-turbine frame of claim 9, wherein the low pressure turbine is connected to a fan through a gearbox.