# US 10,767,488 B1 · Gas turbine engine airfoil frequency design

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- Number: US 10,767,488 B1
- Document ID: US10767488B1
- Status: Granted
- Kind: B1
- Application number: 15/871,197
- Filed: 2018-01-15
- Granted: 2020-09-08
- Earliest claimed: 2017-01-17
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: William R. Edwards; Stephen W. Milks; Steven J. Feigleson; Mark A. Stephens; Joseph C. Straccia
- Web page: https://patentgrep.com/patent/US10767488B1

## CPC

- F01D 5/16: for counteracting blade vibration
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F02C 3/06: the compressor comprising only axial stages (F02C3/10 takes precedence)
- F05D 2220/321: for a special turbine stage
- F05D 2230/80: Repairing, retrofitting or upgrading methods
- F05D 2240/12: Fluid guiding means, e.g. vanes
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F05D 2300/175: Superalloys
- F05D 2300/522: Density
- 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)
- 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 turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and is joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.18-3.48 inch (80.7-88.4 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.17-1.47 inch (29.6-37.3 mm). The airfoil element includes at least two of a first mode with a frequency of 333±10% Hz, a second mode with a frequency of 1554±10% Hz, a third mode with a frequency of 2356±10% Hz, a fourth mode with a frequency of 2830±10% Hz, a fifth mode with a frequency of 4075±10% Hz and a sixth mode with a frequency of 5239±10% Hz.

## Claims

### Claim 1

A turbomachine airfoil element comprising:
an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 3.18-3.48 inch (80.7-88.4 mm);
a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.17-1.47 inch (29.6-37.3 mm); and
at least two of:
a first mode has a frequency of 333 up to ±10% Hz;
a second mode has a frequency of 1554 up to ±10% Hz;
a third mode has a frequency of 2356 up to ±10% Hz;
a fourth mode has a frequency of 2830 up to ±10% Hz;
a fifth mode has a frequency of 4075 up to ±10% Hz; and
a sixth mode has a frequency of 5239 up to ±10% Hz;
wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;
wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a 3T mode, the 1EB, 2EB and 3EB modes correspond to deflections substantially parallel to thickness direction, and the 1T, 2T and 3T modes correspond to twisting about the radial direction;
wherein the airfoil element is part of a stator vane supported by potting at an inner ring;
wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in3 (2.85 g/cm3), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.

### Claim 2 (depends on 1)

The element of claim 1, wherein three of the first, second, third, fourth, fifth, and sixth mode frequencies are present.

### Claim 3 (depends on 1)

The element of claim 1, wherein at a minimum cruise speed of 7700-8600 rpm at Mach 0.8 at 35,000 feet:
the first mode has a frequency of 327 up to ±10% Hz;
the second mode has a frequency of 1527 up to ±10% Hz;
the third mode has a frequency of 2325 up to ±10% Hz;
the fourth mode has a frequency of 2782 up to ±10% Hz;
the fifth mode has a frequency of 4005 up to ±10% Hz; and
the sixth mode has a frequency of 5149 up to ±10% Hz.

### Claim 4 (depends on 1)

The element of claim 1, wherein the frequencies are up to ±5% Hz.

### Claim 5

A method of repairing an airfoil comprising the steps of:
providing an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 3.18-3.48 inch (80.7-88.4), and a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.17-1.47 inch (29.6-37.3 mm), wherein the provided airfoil has at least one unrestored mode frequency that is attributable to damage to the airfoil; and
repairing the airfoil to provide at least two of:
a first mode has a frequency of 333 up to ±10% Hz;
a second mode has a frequency of 1554 up to ±10% Hz;
a third mode has a frequency of 2356 up to ±10% Hz;
a fourth mode has a frequency of 2830 up to ±10% Hz;
a fifth mode has a frequency of 4075 up to ±10% Hz; and
a sixth mode has a frequency of 5239 up to ±10% Hz;
wherein at least one of the first mode frequency, second mode frequency, third mode frequency, fourth mode frequency, fifth mode frequency, and sixth mode frequency corresponds to a restored mode frequency that supersedes the unrestored mode frequency;
wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;
wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a 3T mode, the 1EB, 2EB and 3EB modes correspond to deflections substantially parallel to thickness direction, and the 1T, 2T and 3T modes correspond to twisting about the radial direction;
wherein the airfoil element is part of a stator vane supported by potting at an inner ring;
wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in3 (2.85 g/cm3), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.

### Claim 6

A turbofan engine comprising:
a fan section;
a compressor section arranged fluidly downstream from the fan section;
a turbine section arranged fluidly downstream from the compressor section;
a combustor arranged fluidly between the compressor and turbine sections; and
an airfoil in at least one of the fan, compressor and turbine sections, the airfoil having:
pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction of a span that is in a range of 3.18-3.48 inch (80.7-88.4 mm);
a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% of the span is in a range of 1.17-1.47 inch (29.6-37.3 mm); and
at least two of:
a first mode has a frequency of 333 up to ±10% Hz;
a second mode has a frequency of 1554 up to ±10% Hz;
a third mode has a frequency of 2356 up to ±10% Hz;
a fourth mode has a frequency of 2830 up to ±10% Hz;
a fifth mode has a frequency of 4075 up to ±10% Hz; and
a sixth mode has a frequency of 5239 up to ±10% Hz;
wherein the frequencies are at a zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;
wherein the first mode is a 1EB mode, the second mode is a 1T mode, the third mode is a 2EB mode, the fourth mode is a 2T mode, the fifth mode is a 3EB mode, and the sixth mode is a 3T mode, the 1EB, 2EB and 3EB modes correspond to deflections substantially parallel to thickness direction, and the 1T, 2T and 3T modes correspond to twisting about the radial direction;
wherein the airfoil is provided in the compressor section, the compressor section includes a high pressure compressor fluidly downstream from a low pressure compressor that includes three stages, and the airfoil is in the low pressure compressor, the airfoil element is part of a stator vane supported by potting at an inner ring;
wherein the airfoil is an aluminum-based alloy, the aluminum-based alloy has a density of about 0.103 lb/in3 (2.85 g/cm3), the aluminum-based alloy has a modulus of elasticity of about 10.4 Mpsi (71 GPa) at room temperature.