# US 10,480,535 B2 · Fan rotor with flow induced resonance control

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- Number: US 10,480,535 B2
- Document ID: US10480535B2
- Status: Granted
- Kind: B2
- Application number: 15/465,808
- Filed: 2017-03-22
- Published: 2018-09-27
- Granted: 2019-11-19
- Earliest claimed: 2017-03-22
- Assignees: Pratt & Whitney Canada Corp.
- Applicants: Pratt & Whitney Canada Corp.
- Inventors: Ignatius Theratil; Krishna Balike
- Web page: https://patentgrep.com/patent/US10480535B2

## CPC

- F04D 29/666: {by means of rotor construction or layout, e.g. unequal distribution of blades or vanes}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F01D 5/16: for counteracting blade vibration
- F04D 29/324: {Blades}
- F04D 29/327: {with non identical blades}
- F04D 29/384: {characterised by form}
- F04D 29/668: {damping or preventing mechanical vibrations}
- B64D 27/20: within, or attached to, fuselages
- F05D 2230/10: by removing material
- F05D 2240/303: related to the leading edge of a rotor blade
- F05D 2240/304: related to the trailing edge of a rotor blade
- F05D 2260/961: by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- 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 rotor for a gas turbine is disclosed which includes alternating first and second set of rotor blades, the first set of rotor blades having a baseline profile and the second set of rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode. The cutback may be a leading edge cutback at a span position located a distance away from the hub between 20% and 50% of the total span length. The selected natural vibration mode may be a natural vibration mode higher than the 1st natural vibration mode, more specifically may be the 5th natural vibration mode.

## Claims

### Claim 1

A fan for a gas turbine, the fan comprising fan blades circumferentially distributed around and extending a full span length from a central hub, the fan blades including alternating first fan blades and second fan blades, the first fan blades having a baseline profile and the second fan blades having a modified profile being the same as the baseline profile but for a leading edge cutback, the leading edge cutback extending from a first span position to a second span position, wherein the first span position is located at a distance away from the hub not exceeding 50% of the total span length and the second span position is located at a distance away from the hub exceeding 20% of the total span length, the first span position and the second span position are respectively located radially outwardly of and radially inwardly of a span location corresponding to a maximum deflection point for a selected natural vibration mode of the first fan blades, the selected natural vibration mode is a natural vibration mode higher than a 1st natural vibration mode.

### Claim 2 (depends on 1)

The fan as defined in claim 1, wherein the leading edge cutback removes a portion of the baseline profile surrounding the maximum deflection point and all points of at least 95% of maximum deflection of the selected natural vibration mode.

### Claim 3 (depends on 1)

The fan as defined in claim 1, wherein the leading edge cutback removes a portion of the baseline profile surrounding the maximum deflection point and all points of no less than 65% of maximum deflection of the selected natural vibration mode.

### Claim 4 (depends on 1)

The fan as defined in claim 1, wherein the selected natural vibration mode is a 5th natural vibration mode.

### Claim 5 (depends on 1)

The fan as defined in claim 1, wherein the fan blades are swept fan blades.

### Claim 6 (depends on 1)

The fan as defined in claim 1, the fan blades including successively alternating first, second and third fan blades, the third fan blades having a second modified profile, the second modified profile being the same as the baseline profile but for cutback different from the cutback of the modified profile of the second fan blades.

### Claim 7 (depends on 1)

The fan as defined in claim 1, wherein the maximum deflection point of the first fan blades corresponds to the span-wise location where an anti-node having maximum deflection is located for the selected natural vibration mode generated by flow induced resonance.

### Claim 8

A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a leading edge baseline profile and the second rotor blades having a leading edge profile with a leading edge cutback relative to the baseline profile, the leading edge cutback extending from a first span position to a second span position, wherein the first span position is located at a distance away from the hub not exceeding 50% of the total span length and the second span position is located at a distance away from the hub exceeding 20% of the total span length.

### Claim 9 (depends on 8)

The rotor as defined in claim 8, wherein the first position is located radially outwardly of a span location corresponding to a maximum deflection point for a selected natural vibration mode of a fan blade having a leading edge baseline profile and the second span position is located radially inwardly of the maximum deflection point, the selected natural vibration mode being a natural vibration mode higher than the 1st natural vibration mode.

### Claim 10 (depends on 9)

The rotor as defined in claim 9, wherein the selected natural vibration mode is a 5th natural vibration mode.

### Claim 11 (depends on 8)

The fan as defined in claim 8, wherein the fan blades are swept fan blades.

### Claim 12 (depends on 8)

The rotor as defined in claim 8, wherein the maximum deflection point of the first rotor blades corresponds to the span-wise location where an anti-node having maximum deflection is located for the selected natural vibration mode generated by flow induced resonance.

### Claim 13

A rotor for a gas turbine, the rotor comprising rotor blades circumferentially distributed around and extending a total span length from a central hub, the rotor blades including alternating first rotor blades and second rotor blades, the first rotor blades having a baseline profile and the second rotor blades having a profile with a cutback relative to the baseline profile, the cutback removing a portion of the baseline profile surrounding a maximum deflection point of a selected natural vibration mode, wherein the cutback is located in a leading edge of the second rotor blades and extends from a from a first span position to a second span position, the first span position is located at a distance away from the central hub not exceeding 50% of the total span length and the second span position is located at a distance away from the central hub exceeding 20% of the total span length, and the selected natural vibration mode is a natural vibration mode higher than a 1st natural vibration mode.

### Claim 14 (depends on 13)

The rotor of claim 13, wherein the portion of the baseline profile removed by the cutback surrounds the maximum deflection point and all points of at least 95% of maximum deflection of the selected natural vibration mode.

### Claim 15 (depends on 13)

The rotor of claim 13, wherein the portion of the baseline profile removed by the cutback surrounds the maximum deflection point and all points of no less than 65% of maximum deflection of the selected natural vibration mode.

### Claim 16 (depends on 13)

The rotor as defined in claim 13, wherein the selected natural vibration mode is a 5th natural vibration mode.

### Claim 17 (depends on 13)

The rotor as defined in claim 13, wherein the maximum deflection point of the first rotor blades corresponds to the span-wise location where an anti-node having maximum deflection is located for the selected natural vibration mode generated by flow induced resonance.