MISTUNED LAMINATE AIRFOIL
First Claim
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1. A fan for a gas turbine engine comprising:
- a fan mounting a first group of blades and a second group of blades;
said first group of blades and said second group of blades sharing a profile shapewherein said first group of blades have a first laminate composition;
wherein said second group of blades have a second laminate composition, distinct from the first laminate composition; and
wherein a frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.
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Abstract
A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.
13 Citations
20 Claims
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1. A fan for a gas turbine engine comprising:
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a fan mounting a first group of blades and a second group of blades; said first group of blades and said second group of blades sharing a profile shape wherein said first group of blades have a first laminate composition; wherein said second group of blades have a second laminate composition, distinct from the first laminate composition; and wherein a frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine comprising:
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a compressor section; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor; a fan drivably connected to said turbine section, the fan including a first set of blades and a second set of blades, wherein each of said first set of blades and said second set of blades share a profile; the first set of blades having a first vibratory mode; and the second set of blades having a second vibratory mode distinct form the first vibratory mode. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18)
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19. A method for creating a gas turbine engine fan comprising:
installing a first set of blades and a second set of blades in circumferentially alternating positions about a rim, wherein set first set of blades and said second set of blades share a profile and have distinct vibratory modes. - View Dependent Claims (20)
Specification