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公开(公告)号：US20210207614A1
公开(公告)日：2021-07-08
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：US10294965B2
公开(公告)日：2019-05-21
申请号：US15163990
申请日：2016-05-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , Michael LaMar Trego , John Repp , James Kroeger
IPC: F01D5/16 , F01D5/34 , F02C3/08 , F04D17/02 , F04D19/00 , F04D19/02 , F04D29/32 , F04D29/38 , F04D29/66
Abstract: A blisk fan is provided for a turbine engine propulsion system. The blisk fan includes a hub configured to rotate about a rotational axis at a maximum rotational speed, and a plurality of blades extending radially outward from the hub to define a fan leading edge tip diameter. Each of the blades has a first vibratory mode at a natural frequency, which is greater than a first fan order and less than a second fan order at the maximum rotational speed. The compression system preferably has a balance factor of the compression system between 1.9 and 3.2.
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公开(公告)号：US20160238018A1
公开(公告)日：2016-08-18
申请号：US14623761
申请日：2015-02-17
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Richard David Conner , Michael Todd Barton , Yoseph Gebre-Giorgis , Harry Lester Kington , John Repp
CPC classification number: F04D29/284 , F01D5/225 , F01D9/04 , F02C3/09 , F05D2250/38 , F05D2260/941 , Y02T50/671
Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.
Abstract translation: 如同包含前掠式叶轮的燃气涡轮发动机的实施例一样，提供了前掠式叶轮的实施例。 在一个实施例中，燃气涡轮发动机包括安装在轴上的轴和向前扫掠的叶轮。 前掠式叶轮又包括内侧叶轮部分，外侧叶轮部分，其包围内侧叶轮部分，以及多个轮毂流动路径，其沿前掠式叶轮从内侧叶轮部分延伸到外侧叶轮部分。 多个轮毂流动路径各自具有沿着与流路出口相切的直线沿向前方向倾斜的流路出口。
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14.发明申请公开(公告)号：US20220010682A1
公开(公告)日：2022-01-13
申请号：US16927161
申请日：2020-07-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jeffrey Gluck , Bruce Reynolds , John Repp
Abstract: Systems and methods for air injection passageway integration and optimization in turbomachinery using surface vortex generation. An airfoil including a leading edge, a trailing edge, a pressure side, and a suction side, and is configured to influence an airflow as it passes from the leading edge to the trailing edge. The airfoil defines an aerodynamic passageway having an inlet on the pressure side and an outlet on the suction side to deliver air from the airflow through the airfoil to the suction side. The outlets are configured to inject the air at areas on either airfoil side targeted due to their propensity to generate undesirable boundary layer growth and associated flow losses. Outlet may also be included in the hub and the shroud of the turbomachine.
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公开(公告)号：US20210381380A1
公开(公告)日：2021-12-09
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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Patent Agency Ranking
16.发明申请公开(公告)号：US20200158128A1
公开(公告)日：2020-05-21
申请号：US16198279
申请日：2018-11-21
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David Richard Hanson , John A. Gunaraj , Jeffrey Hayes , Nick Nolcheff , John Repp
IPC: F04D29/38
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, and at 10% of the span of the adjacent ones of the airfoils above or below the spanwise location of the maximum value, the throat dimension is less than 97% of the maximum value. The throat dimension at 5% of the span of the adjacent ones of the airfoils is less than 70% of the maximum value.
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公开(公告)号：US10330121B2
公开(公告)日：2019-06-25
申请号：US14632024
申请日：2015-02-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , David Richard Hanson , John Repp , Michael Todd Barton , John A. Gunaraj
Abstract: Methods and apparatuses are provided for a compressor. The compressor includes a first stage having a first rotor and a first stator, and a second stage downstream from the first stage in a direction of a fluid flow. The compressor also includes a secondary flow system that directs fluid from the second stage into the first stator to improve at least one of a performance and a stability of the compressor.
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公开(公告)号：US20180355791A1
公开(公告)日：2018-12-13
申请号：US16056101
申请日：2018-08-06
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：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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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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