公开(公告)号：US10760580B2

公开(公告)日：2020-09-01

申请号：US15904890

申请日：2018-02-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Nick Nolcheff

IPC: F04D27/02 ,  F04D19/02 ,  F04D29/32 ,  F01D25/24 ,  F04D27/00 ,  F04D29/52 ,  F04D29/68

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.

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.

公开(公告)号：US20200049163A1

公开(公告)日：2020-02-13

申请号：US16656211

申请日：2019-10-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Richard David Conner ,  Bruce David Reynolds ,  Timothy Gentry ,  Peter Hall

IPC: F04D29/56 ,  F01D9/04 ,  F04D27/00 ,  F04D29/02 ,  F04D29/54 ,  F04D29/64 ,  F01D17/16

Abstract: Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance.

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

IPC: F01D9/06 ,  F04D27/02 ,  F04D29/52 ,  F04D29/68

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.

公开(公告)号：US10295436B2

公开(公告)日：2019-05-21

申请号：US15072560

申请日：2016-03-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Richard David Conner ,  Bruce David Reynolds ,  Jonathan C. Bittner ,  Srinivas Jaya Chunduru ,  Bruce D. Wilson

IPC: G01M5/00 ,  G01B11/00 ,  G01M15/14

Abstract: A field deployable, portable structured light measurement (SLM) apparatus, together with a structured light measurement process to manage part to part variation in production and in the field, to support both rotor airfoil mistuning and rotor airfoil repair limits.

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

IPC: F02C3/08 ,  F04D19/02 ,  F04D17/02 ,  F04D29/32 ,  F04D29/54 ,  F04D29/28

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.

公开(公告)号：US20180258770A1

公开(公告)日：2018-09-13

申请号：US15454372

申请日：2017-03-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Richard David Conner ,  Costas Vogiatzis ,  Timothy Gentry

IPC: F01D5/14 ,  B23P15/02

Abstract: A rotor blade comprises a mount and a blade that extends from the mount along a radial axis. The leading edge includes an indent segment. The leading edge has a leading edge radial length measured along the radial axis. The indent segment has an indent radial length measured along the radial axis. The indent segment has an indent depth. A first ratio of the indent radial length to the leading edge radial length is at most 0.5. A second ratio of the indent depth to the indent radial length is at least 0.05.

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

IPC: F04D27/02 ,  F04D29/32 ,  F04D19/02 ,  F04D27/00 ,  F04D29/68 ,  F04D29/52 ,  F01D25/24

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.

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

IPC: F02C3/08 ,  F04D29/54 ,  F04D29/32 ,  F04D17/02 ,  F04D29/28

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.

公开(公告)号：US20170268963A1

公开(公告)日：2017-09-21

申请号：US15072560

申请日：2016-03-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Richard David Conner ,  Bruce David Reynolds ,  Jonathan C. Bittner ,  Srinivas Jaya Chunduru ,  Bruce D. Wilson

IPC: G01M15/14 ,  G01B11/00

CPC classification number: G01M15/14 ,  G01B11/00 ,  G01M5/0016 ,  G01M5/0091

Abstract: A field deployable, portable structured light measurement (SLM) apparatus, together with a structured light measurement process to manage part to part variation in production and in the field, to support both rotor airfoil mistuning and rotor airfoil repair limits.