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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
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Bruce L. Morin , Daniel L. Gysling , Mani Sadeghi
CPC classification number: 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
Abstract: 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：US10823192B2
公开(公告)日：2020-11-03
申请号：US14974151
申请日：2015-12-18
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Daniel L. Gysling
IPC: F04D29/32 , F02K3/06 , F04D29/66 , F04D29/52 , F02C7/36 , F04D19/00 , F04D29/38 , F01D5/16 , F01D5/10 , F01D5/14 , F01D5/30 , F01D5/26 , F02C7/04 , F01D5/02
Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle. The fan blades are provided with at least a first type having a first natural frequency, and a second type having a second natural frequency. The fan rotor has a first mount structure intended for the first type and a distinct second mount structure intended for the second type. The first type of fan blade fits into the first mount structure intended for the first type, but there is a first obstruction preventing the first type of fan blade from being placed into the second mount structure intended for the second type. The second type of fan blade fits into the second mount structure intended for the second type, but there is a second obstruction preventing the second type of fan blade from being placed into the first mount structure intended for the first type.
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公开(公告)号：US20200232390A1
公开(公告)日：2020-07-23
申请号：US16251492
申请日：2019-01-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ramons A. Reba , Bruce L. Morin , Daniel L. Gysling , Carson A. Roy Thill , Jose R. Paulino , JinQuan Xu , Stephen A. Morford
Abstract: A section for a gas turbine engine includes a rotating structure, a stationary structure, and a flow guide assembly arranged generally between the rotating structure and the stationary structure. A flow path is defined between the flow guide assembly and one of the rotating structure and the stationary structure. The flow guide assembly includes a plurality of apertures configured to disrupt acoustic waves of air in the flow path. A seal is configured to establish a sealing relationship between the rotating structure and the stationary structure, and wherein an inlet to the flow path is adjacent the seal. A gas turbine engine and a method of disrupting acoustic waves in a flow path of a gas turbine engine are also disclosed.
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公开(公告)号：US20200209102A1
公开(公告)日：2020-07-02
申请号：US16799281
申请日：2020-02-24
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Joseph V. Paturzo , Richard A. Lomenzo , Allison Nicklous
IPC: G01M7/02 , G01M13/005 , G01M15/14
Abstract: A system is provided for testing a component. This system includes a support structure, an excitation system and a sensor system. The support structure is configured to support the component. The excitation system includes a plurality of excitation devices arranged in an array. The plurality of excitation devices at least include a first excitation device, a second excitation device and a third excitation device. The excitation system is configured to respectively control each of the plurality of excitation devices to excite a vibratory response in the component. The sensor system is configured to output data indicative of the vibratory response.
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Patent Agency Ranking
公开(公告)号：US20180328225A1
公开(公告)日：2018-11-15
申请号：US15592790
申请日：2017-05-11
Applicant: United Technologies Corporation
Inventor： Todd A. Davis , Denman H. James , Daniel L. Gysling , Joseph D. Walker
CPC classification number: F01D25/164 , F01D25/20 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/53 , F05D2260/96 , F05D2260/98 , F16C27/045 , F16C2360/23 , F16F15/0237 , F16K15/00
Abstract: A fluid damping structure is provided that includes a damper ring. The damper ring includes an annular body a plurality of fluid check valves, and at least one fluid stop. The annular body extends circumferentially around an axial centerline, and is defined by a first end surface, a second end surface, an outer radial surface, and an inner radial surface. The outer radial surface and the inner radial surface extend axially from the first end surface toward the second end surface. The body includes one or more check valve passages. Each check valve passage extends axially from an open end disposed at the first end surface inwardly toward the second end surface, and is disposed between the inner radial surface and the outer radial surface. An inlet aperture extends between each check valve passage and the outer radial surface, and an outlet aperture extends between each check valve passage and the inner radial surface. Each fluid check valve is disposed in a check valve passage. The at least one fluid stop is configured to prevent fluid exit from the open end of each check valve passage.
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公开(公告)号：US20180274588A1
公开(公告)日：2018-09-27
申请号：US15470252
申请日：2017-03-27
Applicant: United Technologies Corporation
Inventor： David B. Hudson , Gregory M. Savela , Robert J. Morris , Christopher J. Zuck , Daniel L. Gysling , Alan J. Goetschius
Abstract: A squeeze film damper includes a static member and a whirling member positioned adjacent to the static member. A gap is formed between the static member and the whirling member. A pressurized oil reservoir is formed in the gap between the static member and the whirling member. A first low pressure oil reservoir is formed in a first cavity in the whirling member, wherein the first low pressure oil reservoir is positioned on a first end of the pressurized oil reservoir. A second low pressure oil reservoir is formed in a second cavity in the whirling member, wherein the second low pressure oil reservoir is positioned on a second end of the pressurized oil reservoir. A first primary seal is positioned between the first end of the pressurized oil reservoir and the first low pressure oil reservoir, and a second primary seal is positioned between the second end of the pressurized oil reservoir and the second low pressure oil reservoir.
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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
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ian T. Marchaj , Bruce L. Morin , Mani Sadeghi , Daniel L. Gysling
CPC classification number: F02C7/045 , B64D2033/0206 , F01D25/04 , F01D25/24 , F02K1/827 , F02K3/06 , F05D2220/323 , F05D2260/96 , F05D2260/963 , G10K11/172 , Y02T50/672
Abstract: 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：US20180066535A1
公开(公告)日：2018-03-08
申请号：US15256411
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Glenn N. Levasseur
CPC classification number: F01D21/003 , F01D17/04 , F01D21/14 , F05D2220/32 , F05D2220/36 , F05D2240/30 , F05D2260/83 , F05D2270/334 , F05D2270/808 , G01H1/003 , G01H1/006 , G01M15/14
Abstract: A method of health monitoring of a gas turbine engine includes mounting a detection system configured to detect an aeromechanical damping characteristic of a row of airfoils of a gas turbine. An actual aeromechanical damping characteristic of the row of airfoils is measured with the detection system. An output signal is generated indicative of the actual aeromechanical damping characteristic of the row of airfoils. A current flutter characteristic is determined based on the output signal indicative of the actual aeromechanical damping characteristic of the row of airfoils. An airfoil health monitoring system for gas turbine engine and a gas turbine engine are also disclosed.
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公开(公告)号：US20170350273A1
公开(公告)日：2017-12-07
申请号：US15173065
申请日：2016-06-03
Applicant: United Technologies Corporation
Inventor： Daniel L. Gysling , Gregory M. Savela , John M. Feiereisen , Robert J. Morris
CPC classification number: F01D25/164 , F02C7/06 , F05D2220/32 , F05D2240/50 , F05D2240/581 , F05D2240/60 , F05D2260/96 , F16C19/06 , F16C27/045 , F16C2360/23
Abstract: A bearing assembly is provided. The bearing assembly includes an inner race configured to couple to a shaft, an outer race disposed around the inner race, and a housing disposed around the outer race. The housing and the outer race define an annulus and a buffer region, and the buffer region defines an axial boundary of the annulus.
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