Patents by Inventor Bruce David Reynolds

Bruce David Reynolds has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 10330121
    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.
    Type: Grant
    Filed: February 26, 2015
    Date of Patent: June 25, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, David Richard Hanson, John Repp, Michael Todd Barton, John A. Gunaraj
  • Patent number: 10295436
    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.
    Type: Grant
    Filed: March 17, 2016
    Date of Patent: May 21, 2019
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Bruce David Reynolds, Jonathan C. Bittner, Srinivas Jaya Chunduru, Bruce D. Wilson
  • Publication number: 20180355791
    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.
    Type: Application
    Filed: August 6, 2018
    Publication date: December 13, 2018
    Applicant: Honeywell International Inc.
    Inventors: Nick Nolcheff, John Repp, Bruce David Reynolds, David Richard Hanson
  • Publication number: 20180258770
    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.
    Type: Application
    Filed: March 9, 2017
    Publication date: September 13, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Richard David Conner, Costas Vogiatzis, Timothy Gentry
  • Publication number: 20180231023
    Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.
    Type: Application
    Filed: February 14, 2017
    Publication date: August 16, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Timothy Gentry, Bruce David Reynolds, Nick Nolcheff
  • Patent number: 10046424
    Abstract: Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: August 14, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, John A. Gunaraj, Timothy Gentry
  • Publication number: 20180216632
    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.
    Type: Application
    Filed: January 31, 2017
    Publication date: August 2, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Bruce David Reynolds, Timothy Gentry, Peter Hall
  • Publication number: 20180187690
    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.
    Type: Application
    Filed: February 26, 2018
    Publication date: July 5, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Publication number: 20180094645
    Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
    Type: Application
    Filed: August 24, 2017
    Publication date: April 5, 2018
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Timothy Gentry, Richard David Conner
  • Patent number: 9932985
    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.
    Type: Grant
    Filed: February 3, 2015
    Date of Patent: April 3, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Patent number: 9784285
    Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: October 10, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Timothy Gentry, Richard David Conner
  • Publication number: 20170276070
    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.
    Type: Application
    Filed: March 24, 2016
    Publication date: September 28, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Nick Nolcheff, John Repp, Bruce David Reynolds, David Richard Hanson
  • Publication number: 20170268963
    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.
    Type: Application
    Filed: March 17, 2016
    Publication date: September 21, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Richard David Conner, Bruce David Reynolds, Jonathan C. Bittner, Srinivas Jaya Chunduru, Bruce D. Wilson
  • Publication number: 20170211586
    Abstract: Embodiments of an impeller shroud support for disposition around an impeller are provided, as are embodiments of gas turbine engine including impeller shroud supports. In one embodiment, the impeller shroud support includes a shroud body, a support arm joined to and extending around the shroud body, and a plurality of Mid-Impeller Bleed (MIB) flow passages. Each MIB flow passage includes, in turn, an inlet formed in the shroud body and configured to receive bleed air extracted from the impeller, a throat portion, an outlet formed in the support arm and through which the bleed air is discharged, and a curved intermediate section between the inlet and the outlet. During usage of the impeller shroud support, the curved intermediate section turns the bleed air flowing through the MIB passage in a radially outward direction prior to discharge from the outlet of the MIB flow passage.
    Type: Application
    Filed: January 26, 2016
    Publication date: July 27, 2017
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Raymond Gage, Bruce David Reynolds, Jeffrey D. Harrison, Michael Todd Barton, Mahmoud Mansour, Kent L. Kime
  • Publication number: 20160252098
    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.
    Type: Application
    Filed: February 26, 2015
    Publication date: September 1, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, David Richard Hanson, John Repp, Michael Todd Barton, John A. Gunaraj
  • Publication number: 20160222973
    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.
    Type: Application
    Filed: February 3, 2015
    Publication date: August 4, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Nick Nolcheff
  • Publication number: 20160076548
    Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
    Type: Application
    Filed: September 12, 2014
    Publication date: March 17, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Timothy Gentry, Richard David Conner
  • Publication number: 20160059365
    Abstract: Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component.
    Type: Application
    Filed: August 28, 2014
    Publication date: March 3, 2016
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, John A. Gunaraj, Timothy Gentry