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公开(公告)号：US11885234B2
公开(公告)日：2024-01-30
申请号：US17444065
申请日：2021-07-30
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce D. Reynolds , John Repp
CPC classification number: F01D5/145 , F01D5/225 , F01D9/041 , F05D2220/323 , F05D2240/124 , F05D2240/127
Abstract: A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The turbomachine includes at least one local vortex generator array defined on the suction side so as to extend onto the hub or the shroud. The at least one local vortex generator array is defined downstream of the leading edge.
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公开(公告)号：US11015465B2
公开(公告)日：2021-05-25
申请号：US16363117
申请日：2019-03-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , John Repp , David Richard Hanson , Nick Nolcheff , Darrell K James
Abstract: A compressor section includes a shroud surface and a rotor with a blade tip that opposes the shroud surface. The rotor is configured to rotate within the shroud about an axis of rotation. Moreover, the compressor section includes a serration groove that is recessed into the shroud surface. The serration groove includes a forward portion with a forward transition and a forward surface that faces in the downstream direction. The forward transition is convexly contoured between the shroud surface and the forward surface. The serration groove includes a trailing portion with a taper surface and a trailing transition. The taper surface tapers inward as the taper surface extends from the forward surface to the trailing transition. The trailing transition is convexly contoured between the taper surface and the shroud surface.
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公开(公告)号：US20170343015A1
公开(公告)日：2017-11-30
申请号：US15163990
申请日：2016-05-25
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , Michael LaMar Trego , John Repp , James Kroeger
CPC classification number: F04D29/668 , F01D5/16 , F01D5/34 , F02C3/08 , F04D17/025 , F04D19/002 , F04D19/02 , F04D29/321 , F04D29/325 , F04D29/328 , F04D29/38 , F04D29/666 , F05D2220/30 , F05D2220/36 , F05D2260/96 , Y02T50/671 , Y02T50/673
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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4.发明授权公开(公告)号：US11608744B2
公开(公告)日：2023-03-21
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：US11371354B2
公开(公告)日：2022-06-28
申请号：US16892152
申请日：2020-06-03
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Nick Nolcheff , John Repp , Bruce Reynolds , John Gunaraj
IPC: F01D5/14
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 having a leading edge, a trailing edge and a mean camber line. The airfoil has a delta inlet blade angle defined as a difference between a local inlet blade angle defined in a spanwise location, and a root inlet blade angle defined at the root. The delta inlet blade angle decreases in the spanwise direction from the root to a minimum value at greater than 10% span and from the minimum value, the delta inlet blade angle increases 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 or the fan.
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Patent Agency Ranking
公开(公告)号：US20240183274A1
公开(公告)日：2024-06-06
申请号：US18408260
申请日：2024-01-09
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce D. Reynolds , John Repp
CPC classification number: F01D5/145 , F01D5/225 , F01D9/041 , F05D2220/323 , F05D2240/124 , F05D2240/127
Abstract: A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The at least one airfoil has a chord that is 0% chord at the leading edge and 100% chord at the trailing edge, and a span defined as 0% at the hub and 100% at the shroud. The turbomachine includes at least one local vortex generator array defined onto the hub between 0% chord to −10% chord at 0% span so as to extend forward of the leading edge.
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公开(公告)号：US20230036499A1
公开(公告)日：2023-02-02
申请号：US17444065
申请日：2021-07-30
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce D. Reynolds , John Repp
Abstract: A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The turbomachine includes at least one local vortex generator array defined on the suction side so as to extend onto the hub or the shroud. The at least one local vortex generator array is defined downstream of the leading edge.
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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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