# US 2016/0251968 A1 · Gas turbine engine airfoil cooling configuration with pressure gradient separators

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- Number: US 2016/0251968 A1
- Document ID: US20160251968A1
- Status: Published application
- Kind: A1
- Application number: 14/632,485
- Filed: 2015-02-26
- Published: 2016-09-01
- Earliest claimed: 2015-02-26
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: San Quach; Ryan Alan Waite; Christopher King; Steven Bruce Gautschi
- Web page: https://patentgrep.com/patent/US20160251968A1

## CPC

- F01D 5/187: {Convection cooling}
- F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20)
- F01D 25/30: Exhaust heads, chambers, or the like
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F05D 2220/32: in gas turbines
- F05D 2240/122: related to the trailing edge of a stator vane
- F05D 2240/127: Vortex generators, turbulators, or the like, for mixing
- F05D 2240/304: related to the trailing edge of a rotor blade
- F05D 2240/307: related to the tip of a rotor blade
- F05D 2240/35: Combustors or associated equipment
- F05D 2240/55: Seals
- F05D 2260/221: Improvement of heat transfer
- F05D 2260/2212: by creating turbulence
- F05D 2260/2214: by increasing the heat transfer surface
- 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)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- 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

An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

## Claims

### Claim 1

An airfoil for a gas turbine engine comprising:
an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface extending in a radial direction from a platform to a tip;
a cavity provided between the pressure and suction side walls near the trailing edge, the cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another, the first and second exit regions are respectively in low and high pressure regions relative to one another; and
first and second pedestal groups respectively arranged at the first and second exit regions, the second pedestal group has first and second pedestals each terminating in an end, the ends of the second pedestals extend beyond the ends of first pedestals.

### Claim 2 (depends on 1)

The airfoil according to claim 1, wherein the airfoil is a blade.

### Claim 3 (depends on 1)

The airfoil according to claim 1, wherein the airfoil extends from the leading edge to the trailing edge in a chord-wise direction, the cavity is provided in at least the last 20% of the airfoil near the trailing edge in the chord-wise direction.

### Claim 4 (depends on 3)

The airfoil according to claim 3, wherein the interior region includes a third pedestal group interconnecting the pressure and suction sidewalls.

### Claim 5 (depends on 4)

The airfoil according to claim 4, wherein the first exit region is provided at the trailing edge.

### Claim 6 (depends on 5)

The airfoil according to claim 5, wherein the first pedestal group is recessed from the trailing edge or extending to the trailing edge.

### Claim 7 (depends on 4)

The airfoil according to claim 4, wherein the second exit region is provided at the tip.

### Claim 8 (depends on 7)

The airfoil according to claim 7, wherein the second pedestal group is recessed from the tip.

### Claim 9 (depends on 1)

The airfoil according to claim 1, wherein a natural flow direction extends from the interior region to the first exit region, and a desired flow direction extends from the interior region to the second exit region, and the ends of the second pedestals extend beyond the ends of first pedestals in the desired flow direction.

### Claim 10 (depends on 9)

The airfoil according to claim 9, wherein the natural flow direction corresponds to an aft direction in the chord-wise direction.

### Claim 11 (depends on 10)

The airfoil according to claim 10, wherein the desired flow direction corresponds to the radial direction.

### Claim 12 (depends on 1)

The airfoil according to claim 1, wherein the first and second pedestals include first and second lengths respectively and first and second widths respectively, the first and second lengths greater than their corresponding first and second widths.

### Claim 13 (depends on 12)

The airfoil according to claim 12, wherein the first and second pedestals are in alternating relationship with one another.

### Claim 14 (depends on 13)

The airfoil according to claim 13, wherein at least one first pedestal is arranged between adjacent second pedestals.

### Claim 15 (depends on 12)

The airfoil according to claim 12, wherein the first length has a ratio relative to the first width of 1<L1/W1<20 and the second length has a ratio relative to the second width of 1<L2/W2<20.

### Claim 16

A component for a gas turbine engine comprising:
a structure including spaced apart walls that provide an exterior surface extending in first and second directions to first and second edges, respectively;
a cavity provided between the walls near the first and second edges, the cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another that terminate at the first and second edges arranged at an angle in a range of 60°-120°, the first and second exit regions respectively in low and high pressure regions relative to one another;
first and second pedestal groups respectively arranged at the first and second exit regions, the second pedestal group has first and second pedestals each terminating in an end, the ends of the second pedestals extend beyond the ends of first pedestals; and
wherein the first and second pedestals include first and second lengths respectively and first and second widths respectively, the first and second lengths greater than their corresponding first and second widths, wherein the first and second pedestals are in alternating relationship with one another.

### Claim 17 (depends on 16)

The component according to claim 16, wherein first and second edge are arranged at about 90° relative to one another.

### Claim 18 (depends on 16)

The component according to claim 16, wherein at least one first pedestals is arranged between adjacent second pedestals.

### Claim 19 (depends on 16)

The component according to claim 16, wherein the first and second pedestal groups are recessed respectively from the first and second edges.

### Claim 20 (depends on 16)

The component according to claim 16, wherein the structure is one of a vane, a blade, a blade outer air seal, a combustor liner or an exhaust liner.

### Claim 21 (depends on 20)

The component according to claim 20, wherein the structure is an airfoil of a blade.

### Claim 22 (depends on 16)

The component according to claim 16, wherein a natural flow direction extends from the interior region to the first exit region, and a desired flow direction extends from the interior region to the second exit region, and the ends of the second pedestals extend beyond the ends of first pedestals in the desired flow direction.