# US 8,770,936 B1 · Turbine blade with near wall cooling channels

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- Number: US 8,770,936 B1
- Document ID: US8770936B1
- Status: Granted
- Kind: B1
- Application number: 12/951,584
- Filed: 2010-11-22
- Granted: 2014-07-08
- Earliest claimed: 2010-11-22
- Assignees: Florida Turbine Technologies, Inc.
- Applicants: George Liang
- Inventors: George Liang
- Web page: https://patentgrep.com/patent/US8770936B1

## CPC

- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 5/187: {Convection cooling}
- F05D 2250/185: serpentine-like
- F05D 2260/202: by film cooling
- F05D 2260/204: by the use of microcircuits
- 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

## Abstract

A turbine rotor blade with a thin thermal skin bonded over a spar to enclose serpentine flow cooling channels that extend from a platform to a blade tip along the airfoil walls. The radial channels discharge into a collection cavity and then flow through exit holes in the trailing edge. The radial cooling channels are formed as semi-circular shaped channels to maximize surface area on the hot side wall and on the cold side wall of the spar.

## Claims

### Claim 1

A turbine rotor blade comprising:
a spar forming a cooling air collection cavity on an inside and a number of serpentine radial flow cooling channels on an outer surface;
a thin thermal skin bonded to the outer surface of the spar to enclose the serpentine radial flow cooling channels;
a row of exit holes on the trailing edge connected directly to the cooling air collection cavity;
the radial flow cooling channels have a semi-circular shape with a flat face against the thin thermal skin; and,
the upward flowing channel and the downward flowing channel form a half-circular shape with a rib separating the two channels.

### Claim 2 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the serpentine radial flow cooling channels are two-pass serpentine flow channels with a first channel being an upward flowing channel and a second channel being a downward flowing channel.

### Claim 3 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
an inner surface of the spar that forms the semi-circular radial flow cooling channels has a semi-circular shape.

### Claim 4 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the serpentine radial flow cooling channels extend from a platform to a tip of the blade.

### Claim 5 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the serpentine radial flow cooling channels discharge into the collection cavity.

### Claim 6 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the thin thermal skin has a roughened surface on a side forming the enclosed radial cooling channels.

### Claim 7 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the serpentine radial flow cooling channels extends from a trailing edge region along the pressure side wall and suction side wall and around the leading edge region of the blade.

### Claim 8 (depends on 1)

The turbine rotor blade of claim 1, and further comprising:
the thin thermal skin has a thickness of 0.010 to 0.030 inches.