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公开(公告)号：US10428685B2
公开(公告)日：2019-10-01
申请号：US15452627
申请日：2017-03-07
发明人： Bruce L. Morin , Daniel L. Gysling , Mani Sadeghi
摘要： Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as ftarget=fS,ND+Ω·ND wherein fS,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and Ω is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R≥2ρc −3ρc≤X≤−0.6ρc wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, ρ is air density, and c is speed of sound.
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公开(公告)号：US20180258853A1
公开(公告)日：2018-09-13
申请号：US15452604
申请日：2017-03-07
CPC分类号： F02C7/045 , B64D2033/0206 , F01D25/04 , F01D25/24 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
摘要： Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.
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公开(公告)号：US10330111B2
公开(公告)日：2019-06-25
申请号：US15126371
申请日：2015-03-30
发明人： Scott C. Billings , Michael K. Gottschalk , William D. Owen , Edward J. Gallagher , Darryl Whitlow , Sue-Li Chuang , Mani Sadeghi
摘要： In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
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公开(公告)号：US20180258788A1
公开(公告)日：2018-09-13
申请号：US15452627
申请日：2017-03-07
发明人： Bruce L. Morin , Daniel L. Gysling , Mani Sadeghi
CPC分类号： F01D25/06 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C7/045 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2240/14 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
摘要： Disclosed is flutter damper including a first cavity having a radially inner side in fluid communication with a flow path, and a second cavity having a radially inner side in fluid communication with a radially outer side of the first cavity, and the flutter damper having an impedance characteristic at one or more target frequencies defined as ftarget=fS,ND+Ω·ND wherein fS,ND is a resonance frequency corresponding to a structural mode of a rotating component, ND is a nodal diameter count of the structural mode, and Ω is a rotational speed of the rotating component, and wherein the flutter damper has the following impedance characteristic at the one or more targeted frequencies R≥2ρc −3ρc≤X≤−0.6ρc wherein R is the real part of the impedance characteristic, X is the imaginary part of the impedance characteristic, ρ is air density, and c is speed of sound.
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公开(公告)号：US20170122336A1
公开(公告)日：2017-05-04
申请号：US15126371
申请日：2015-03-30
发明人： Scott C. Billings , Michael K. Gottschalk , William D. Owen , Edward J. Gallagher , Darryl Whitlow , Sue-Li Chuang , Mani Sadeghi
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/35 , F05D2250/70 , Y02T50/672 , Y02T50/673
摘要： In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
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公开(公告)号：US10519859B2
公开(公告)日：2019-12-31
申请号：US15452604
申请日：2017-03-07
摘要： Disclosed is a flutter damper, including an acoustic liner having a perforated radial inner face sheet and a radial outer back sheet, the acoustic liner being configured for peak acoustical energy absorption at a frequency range that is greater than a frequency range associated with fan flutter, a chamber secured to the radial outer back sheet, the chamber being in fluid communication with the acoustic liner, and the chamber being configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and at least one stiffening structure connected to a top surface of the chamber that tunes the top surface out of the frequency range associated with one or more fan flutter modes.
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