# US 11,028,714 B2 · Fan platform wedge seal

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- Number: US 11,028,714 B2
- Document ID: US11028714B2
- Status: Granted
- Kind: B2
- Application number: 16/036,038
- Filed: 2018-07-16
- Published: 2020-01-16
- Granted: 2021-06-08
- Earliest claimed: 2018-07-16
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Colin J. Kling
- Web page: https://patentgrep.com/patent/US11028714B2

## CPC

- F01D 5/22: Blade-to-blade connections, {e.g. for damping vibrations}
- F01D 11/008: {by spacer elements between the blades, e.g. independent interblade platforms}
- F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28})
- F01D 5/3007: {of axial insertion type}
- F04D 29/322: {Blade mountings}
- F04D 29/329: {Details of the hub}
- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F05D 2220/36: specially adapted for the fan of turbofan engines
- F05D 2240/20: Rotors
- F05D 2240/55: Seals
- F05D 2240/80: Platforms for stationary or moving blades
- F05D 2250/11: triangular
- F05D 2250/181: ridged
- F05D 2250/183: zigzag
- F05D 2250/73: asymmetric
- F05D 2300/43: Synthetic polymers, e.g. plastics; Rubber
- F05D 2300/603: Composites; e.g. fibre-reinforced
- 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)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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)
- 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 rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.

## Claims

### Claim 1

A fan rotor comprising:
a fan hub and a plurality of fan blades extending radially outwardly from said fan hub, platforms positioned intermediate blade sides of adjacent ones of said fan blades;
seals positioned between said blade sides and platform sides of said platforms, said seals having an elongated bonding area bonded to one of said platform sides and said fan blade sides, and said seal having a wedge portion radially outwardly from said elongated bonding area, and there being at least one undulation between said elongated bonding area and said wedge portion; and
wherein there are a plurality of said at least one undulation, and said elongated bonding area extends into a first said undulation, with said first undulation extending circumferentially away from said elongated bonding area to a first end, and a second said undulation extending back from said first end in a direction opposed to said first undulation, and said second undulation extending to said wedge portion, and said wedge portion having side edges and wherein a distance between said side edges increases in thickness in a direction moving radially inwardly, such that said wedge portion provides a seal between said blade and platform sides.

### Claim 2 (depends on 1)

The fan rotor as set forth in claim 1, wherein said seals are formed of a silicone material.

### Claim 3 (depends on 2)

The fan rotor as set forth in claim 2, wherein said platforms are formed of a composite material.

### Claim 4 (depends on 1)

The fan rotor as set forth in claim 1, wherein there is at least a third undulation between said second undulation and said wedge portion.

### Claim 5 (depends on 1)

The fan rotor as set forth in claim 1, wherein said elongated bonding area is attached to one of said platform sides.

### Claim 6 (depends on 5)

The fan rotor as set forth in claim 5, wherein said platform sides extend radially inwardly and with a direction circumferentially toward an opposed one of said platform sides, and wherein a bond area between said platform sides and said elongated bonding area of said seal is along said platform side.

### Claim 7 (depends on 1)

The fan rotor as set forth in claim 1, wherein said wedge portion moves radially outwardly during rotation of said fan rotor.

### Claim 8 (depends on 1)

The fan rotor as set forth in claim 1, wherein said second undulation extends to a second bend which bends circumferentially in an opposed direction from said second undulation to said wedge portion.

### Claim 9

A fan rotor comprising:
a fan hub and a plurality of fan blades extending radially outwardly from said fan hub, platforms positioned intermediate blade sides of adjacent ones of said fan blades;
seals positioned between said blade sides and platform sides of said platforms, said seals having an elongated bonding area bonded to one of said platform sides and said fan blade sides, and said seal having a wedge portion radially outwardly from said elongated bonding area; and
wherein said wedge portion has a hollow portion to provide increased deformability.

### Claim 10 (depends on 9)

The fan rotor as set forth in claim 9, wherein said hollow portion includes a filler.

### Claim 11

A gas turbine engine comprising:
a fan connected for delivering air into a bypass duct and into a compressor section, said compressor section being connected to provide air into a combustor, said combustor being connected to provide products of combustion across a turbine section, said turbine section being operable to drive said compressor section and said fan section, with a turbine rotor in said turbine section driving a fan hub of said fan section;
said fan hub having a plurality of fan blades extending radially outwardly from said fan hub, platforms positioned intermediate blade sides of adjacent ones of said fan blades;
seals positioned between said blade sides and platform sides of said platforms, said seals having a relatively elongated bonding area bonded to one of said platform sides and said fan blade sides, and said seal having a wedge portion radially outwardly from said elongated bonding area, and there being an undulation between said elongated bonding area and said wedge portion; and
wherein there are a plurality of said at least one undulation, and said elongated bonding area extending into a first said undulation, with said first undulation extending circumferentially away from said elongated bonding area to a first end, and a second said undulation extending back from said first end in a direction opposed to said first undulation, and said second undulation extending to the wedge portion and said wedge portion having side edges and wherein a distance between said side edges increases in thickness in a direction moving radially inwardly, such that said wedge portion provides a seal between said blade and platform sides.

### Claim 12 (depends on 11)

The gas turbine engine as set forth in claim 11, wherein said seals are formed of a silicone material, and said platforms are formed of a composite material.

### Claim 13 (depends on 12)

The gas turbine engine as set forth in claim 12, wherein said fan blades are formed of a metallic material.

### Claim 14 (depends on 11)

The gas turbine engine as set forth in claim 11, wherein said elongated bonding area is attached to one of said platform sides.

### Claim 15 (depends on 14)

The gas turbine engine as set forth in claim 14, wherein said platform sides extend radially inwardly and with a direction circumferentially toward an opposed one of said platform sides, and wherein a bond area between said platform sides and said elongated bonding area of said seal is along said platform side.

### Claim 16 (depends on 11)

The gas turbine engine as set forth in claim 11, wherein said wedge portion has a hollow portion.

### Claim 17 (depends on 11)

The gas turbine engine as set forth in claim 11, wherein said turbine rotor drives a fan hub through a gear reduction.