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公开(公告)号：US20180238341A1
公开(公告)日：2018-08-23
申请号：US15439430
申请日：2017-02-22
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , John Repp , Jeffrey Hayes , John A Gunaraj , Yoseph Gebre-Giorgis
CPC classification number: F04D29/325 , B64C11/14 , B64D33/02 , B64D2033/0233 , F01D5/021 , F01D5/141 , F01D5/34 , F02C7/05 , F02K3/06 , F04D29/34 , F04D29/541 , F05D2220/323 , F05D2220/36 , F05D2240/12 , F05D2240/20 , Y02T50/671 , Y02T50/673
Abstract: Embodiments of a core-protecting fan module are provided, as are embodiments of a turbofan engine containing such a fan module. In an embodiment, the core-protecting fan module contains a nose member, a fan rotor downstream of the nose member, a full span stator downstream of the fan rotor, and a splitter structure downstream of the fan rotor. The fan rotor includes a plurality of fan blades, which extends from a rotor hub and which is angularly spaced about a rotational axis. Certain fundamental angular relationships are observed between the angles formed by rotational axis, the nose member, the fan rotor, and a leading edge of the splitter structure to reduce contaminant ingestion by the core flow path and to promote moisture shedding to reduce susceptibility to icing within the fan module, while further avoiding or minimizing negative impacts to other structural and functional aspects of the turbofan engine.
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32.发明申请公开(公告)号：US20180187690A1
公开(公告)日：2018-07-05
申请号：US15904890
申请日：2018-02-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Nick Nolcheff
CPC classification number: F04D27/02 , F01D25/24 , F04D19/02 , F04D27/001 , F04D27/0261 , F04D29/321 , F04D29/526 , F04D29/685 , F05D2220/32 , F05D2230/00
Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.
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公开(公告)号：US20170276070A1
公开(公告)日：2017-09-28
申请号：US15079538
申请日：2016-03-24
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , John Repp , Bruce David Reynolds , David Richard Hanson
CPC classification number: F02C3/08 , F04D17/025 , F04D19/02 , F04D29/286 , F04D29/321 , F04D29/542 , F05D2220/32 , F05D2220/3216 , F05D2240/35
Abstract: Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.
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公开(公告)号：US09631554B2
公开(公告)日：2017-04-25
申请号：US14154428
申请日：2014-01-14
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeff Howe , Harry Lester Kington , Nick Nolcheff
CPC classification number: F02C7/052 , B03C3/08 , B03C3/12 , B03C3/361 , B03C3/41 , B03C2201/10 , B64D2033/0246 , F05D2260/607 , F23R3/04 , Y02T50/675
Abstract: An inlet particle separator system for an engine includes an inner flowpath section, an outer flowpath section, a splitter, a first electrostatic discharge device, and a second electrostatic discharge device. The outer flowpath section surrounds at least a portion of the inner flowpath section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The first electrostatic charge device is disposed between the air inlet and the splitter and is electrostatically charged to a first polarity. The second electrostatic charge device is disposed downstream of the first electrostatic charge device and is electrostatically charged to a second polarity that is opposite to the first polarity.
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35.发明申请GAS TURBINE ENGINE COMPRESSORS HAVING OPTIMIZED STALL ENHANCEMENT FEATURE CONFIGURATIONS AND METHODS FOR THE PRODUCTION THEREOF 有权具有优化强化特征的燃气发动机发动机压缩机特征及其生产方法公开(公告)号：US20160222973A1
公开(公告)日：2016-08-04
申请号：US14612404
申请日：2015-02-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Nick Nolcheff
CPC classification number: F04D27/02 , F01D25/24 , F04D19/02 , F04D27/001 , F04D27/0261 , F04D29/321 , F04D29/526 , F04D29/685 , F05D2220/32 , F05D2230/00
Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.
Abstract translation: 提供具有优化的失速增强特征（SEF）构造的多级燃气轮机（GTE）压缩机，以及用于生产它的方法。 多级GTE压缩机包括一系列轴向压缩机级，每个轴向压缩机级包含安装在燃气涡轮发动机的轴上的转子。 在一个实施例中，该方法包括选择分布在燃气涡轮发动机的运行速度范围内的多个发动机转速的步骤或过程，在每个所选择的发动机转速下识别一个或多个失速限制转子，建立SEF配置 在对应于失速限制转子的选定位置将多个SEF集成到多级GTE压缩机中，并根据优化的SEF配置生产多级GTE压缩机。
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Patent Agency Ranking
36.发明公开公开(公告)号：US20240352896A1
公开(公告)日：2024-10-24
申请号：US18303111
申请日：2023-04-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Nick Nolcheff , Ryan Bernaud , Greyson Boyll
CPC classification number: F02C9/18 , F02C3/08 , F02C9/20 , F02C9/22 , F04D27/0223 , F04D27/0246 , F05D2270/101 , F05D2270/304
Abstract: Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.
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37.发明授权公开(公告)号：US11421544B2
公开(公告)日：2022-08-23
申请号：US17090039
申请日：2020-11-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Nick Nolcheff
Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.
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公开(公告)号：US11378093B2
公开(公告)日：2022-07-05
申请号：US17060219
申请日：2020-10-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David Richard Hanson , John A. Gunaraj , Jeffrey Hayes , Nick Nolcheff , John Repp
Abstract: A rotor for a compressor includes a hub and a plurality of airfoils having a root, a tip opposite the root and a span that extends from 0% at the root to 100% at the tip. Each of the airfoils is coupled to the hub at the root and is spaced apart from adjacent ones of the airfoils over the span by a throat dimension. The throat dimension has a maximum value at a spanwise location between 60% of the span and 90% of the span of the adjacent ones of the airfoils. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.
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公开(公告)号：US11286779B2
公开(公告)日：2022-03-29
申请号：US16892145
申请日：2020-06-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , John Repp , Bruce Reynolds , John Gunaraj
Abstract: A rotor for a turbofan booster section associated with a fan section of a gas turbine engine includes a rotor blade having an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a plurality of chord lines spaced apart in a spanwise direction. Each chord line of the plurality of chords lines is defined between the leading edge and the trailing edge and has a normalized chord value. From the hub, the normalized chord value decreases to a minimum value between about 20% to about 90% span and increases from the minimum value to the tip. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to the shaft or the fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and fan.
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公开(公告)号：US11181120B2
公开(公告)日：2021-11-23
申请号：US16198266
申请日：2018-11-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , Jeffrey Hayes , John A. Gunaraj , Yoseph Gebre-Giorgis , David Richard Hanson , John Repp
Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil extending from a root to a tip and having a leading edge and a trailing edge. The airfoil has a span that extends from 0% at the root to 100% at the tip and a mean camber line that extends from the leading edge to the trailing edge. The airfoil has a total camber distribution that increases from the root to a maximum value of total camber between 5% of the span and 20% of the span.
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