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    High performance wedge diffusers for compression systems
    21.
    发明授权
    High performance wedge diffusers for compression systems 有权

    公开(公告)号：US11333171B2

    公开(公告)日：2022-05-17

    申请号：US16951258

    申请日：2020-11-18

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shakeel Nasir ,  Nick Nolcheff ,  Cristopher Frost

    IPC: F04D29/44

    Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.

    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR
    22.
    发明申请
    CHARACTERISTIC DISTRIBUTION FOR ROTOR BLADE OF BOOSTER ROTOR 有权

    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

    IPC: F01D5/02 ,  F02C7/36 ,  F01D5/30

    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.

    Gas turbine engine particulate ingestion and accumulation sensor system and method
    23.
    发明授权
    Gas turbine engine particulate ingestion and accumulation sensor system and method 有权

    公开(公告)号：US11149583B2

    公开(公告)日：2021-10-19

    申请号：US16834112

    申请日：2020-03-30

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Dave Dischinger ,  Nick Nolcheff

    IPC: F01D21/00 ,  F01D17/02 ,  F01D21/10 ,  F02C7/05 ,  G01M15/14

    Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing the number, size, and type of particulate at a first position on the gas turbine engine and supplying first data representative thereof, where the first position located at a first side of a gas turbine engine component; sensing the number, size, and type of particulate at a second position on the gas turbine engine and supplying first data representative thereof, where the second position located at a second side of the gas turbine engine component and downstream of the first position; and processing the first data and the second data to determine the mass of the particulate accumulated on the gas turbine engine component.

    Diffuser assemblies for compression systems
    24.
    发明授权
    Diffuser assemblies for compression systems 有权

    公开(公告)号：US10989219B2

    公开(公告)日：2021-04-27

    申请号：US16266484

    申请日：2019-02-04

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Shakeel Nasir ,  Nick Nolcheff ,  Cristopher Frost

    IPC: F04D29/44 ,  F04D29/22

    Abstract: Circumferentially-split diffuser assemblies utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the diffuser assembly includes flow passages, which extend through the diffuser assembly and which include diffuser flow passage sections. Diffuser airfoils are interspersed with the diffuser flow passage sections. The diffuser airfoils include inboard and outboard airfoil segments distributed around a diffuser assembly centerline. The inboard and outboard airfoil segments are contained in and, thus, defined by inner and outer annular diffuser structures, respectively. The outer annular diffuser structure circumscribes the inner annular diffuser structure. In certain cases, the inboard airfoil segments and at least a portion of inner annular diffuser structure are composed of a first material, while the outboard airfoil segments and at least a portion of outboard annular diffuser structure are composed of a second material different than the first material.

    MULTISTAGE AXIAL-CENTRIFUGAL COMPRESSOR SYSTEMS AND METHODS FOR MANUFACTURE
    26.
    发明申请
    MULTISTAGE AXIAL-CENTRIFUGAL COMPRESSOR SYSTEMS AND METHODS FOR MANUFACTURE 审中-公开

    公开(公告)号：US20200256192A1

    公开(公告)日：2020-08-13

    申请号：US16269804

    申请日：2019-02-07

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Bruce David Reynolds ,  Richard David Conner ,  Michael T. Barton ,  Jeffrey W. Gluck ,  Nick Nolcheff

    IPC: F01D5/06

    Abstract: A method of manufacturing a multistage axial-centrifugal compressor for a gas turbine engine and a multistage axial-centrifugal compressor that includes a series of axial compressor stages each having a rotor mounted to a common shaft positioned upstream from a centrifugal compressor stage mounted to the common shaft. The method includes determining an operational rotor tip speed for each of the axial stages. The method includes comparing the operational rotor tip speed to a threshold range value and determining to machine an airfoil of the rotor for at least one of the axial stages by an arbitrary manufacturing approach based on the operational rotor tip speed as greater than the threshold range value. The method includes determining to machine an airfoil of the rotor for at least one of the axial stages by a flank manufacturing approach based on the operational rotor tip speed as less than the threshold range value.

    THROAT DISTRIBUTION FOR A ROTOR AND ROTOR BLADE HAVING CAMBER AND LOCATION OF LOCAL MAXIMUM THICKNESS DISTRIBUTION
    27.
    发明申请
    THROAT DISTRIBUTION FOR A ROTOR AND ROTOR BLADE HAVING CAMBER AND LOCATION OF LOCAL MAXIMUM THICKNESS DISTRIBUTION 审中-公开

    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.

    PROPULSION AND ELECTRIC POWER GENERATION SYSTEM
    29.
    发明申请
    PROPULSION AND ELECTRIC POWER GENERATION SYSTEM 审中-公开

    公开(公告)号：US20190061962A1

    公开(公告)日：2019-02-28

    申请号：US15683484

    申请日：2017-08-22

    Applicant: HONEYWELL INTERNATIONAL INC.

    Inventor： Nick Nolcheff ,  John Meier ,  James Laffan ,  Alan D. Hemmingson ,  Cristian Anghel

    IPC: B64D27/10 ,  B64D41/00 ,  F02C7/32

    Abstract: A propulsion and electric power generation system includes a dual-spool turbofan gas turbine engine and an electrical generator. The dual-spool turbofan gas turbine engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool. The low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and is disposed downstream of the low-pressure turbine. A first fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the fan for propulsive power generation (Pt). A second fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the electrical generator for electrical power generation (Pe). A ratio of Pe to Pt (Pe/Pt), during operation of the dual-spool turbofan gas turbine engine, controllably spans a range from less than about 0.06 to at least 0.18.

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