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US 12,012,865 B2Granted
Tailored material property tuning for turbine engine fan blades
AssigneesRolls-Royce North American Technologies Inc., ROLLS-ROYCE plc
InventorsMichael Glavicic, Daniel E. Molnar, Jr., Matthew Jordan, Michael Meyer
Life of this patent
Estimating the term…
Abstract
Methods for forming a blade for a gas turbine engine include altering the crystallographic texture of the blade in a discrete region relative to the surrounding locations of the blade to minimize flutter and/or mistune the blade by changing the natural frequency response of at least one mode of the blade.
Claims16
A method of making a blade for a gas turbine engine, the method comprising
- calculating a strain profile for a first natural frequency of a virtual blade having a predetermined shape, the strain profile correlating to a deflection of the virtual blade vibrating at the first natural frequency,
- identifying a first discrete region of the virtual blade,
- applying at least one of heat and a force to a first discrete region of a stock of material, and
- forming a physical blade having the predetermined shape from the stock of material such that the first discrete region of the stock of material forms a first region of the physical blade that corresponds in location with the first discrete region of the virtual blade so that at least one of a first natural frequency of the physical blade corresponding to the first natural frequency of the virtual blade and a deflection of the physical blade at the first natural frequency of the physical blade is different from at least one of the first natural frequency of the virtual blade and the deflection of the virtual blade at the first natural frequency of the virtual blade,
- further comprising determining a second natural frequency of the virtual blade and the step of identifying the first discrete region of the virtual blade includes identifying a discrete region of the virtual blade in which the first natural frequency of the physical blade will be altered more than a second natural frequency of the physical blade that corresponds with the second natural frequency of the virtual blade.
2 more elements
A method of making a blade for a gas turbine engine, the method comprising
- determining a strain profile of a blade having a first crystallographic texture profile for a first natural frequency of the blade,
- identifying a first discrete region of the blade in which the strain profile has a greatest magnitude of strain based on the strain profile, and
- treating the blade at or adjacent the first discrete region to alter the first crystallographic texture profile of the blade around the first discrete region such that the blade has a second crystallographic texture profile that is different from the first crystallographic texture profile and change an elastic modulus of the blade around the first discrete region to modify at least one of a deflection of the blade and the first natural frequency of the blade,
- further comprising determining a second natural frequency of the blade and the step of treating the first discrete region causes the first natural frequency to change in magnitude greater than it causes a change in magnitude of the second natural frequency of the blade.
1 more element
A method of making a blade for a gas turbine engine, the method comprising
- determining a first natural frequency associated with a first vibrational mode of a blade, and
- treating the blade at a first discrete region to alter a crystallographic texture of the blade at the first discrete region to alter at least one of a deflection of the blade at the first natural frequency and the first natural frequency of the blade,
- further comprising determining a second natural frequency associated with a second vibrational mode of the blade and the first discrete region is chosen to cause the first natural frequency of the blade to change in magnitude greater than a change in the second natural frequency of the blade.
Dependencies are inferred from the claim text.