公开(公告)号：US10907503B2

公开(公告)日：2021-02-02

申请号：US16108907

申请日：2018-08-22

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  Jong Lee

IPC: F01D25/24 ,  F01D9/04 ,  F02C9/18 ,  F04D27/02 ,  F04D29/54

Abstract: A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.

公开(公告)号：US20200208532A1

公开(公告)日：2020-07-02

申请号：US16235876

申请日：2018-12-28

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Nick Nolcheff

IPC: F01D11/12

Abstract: A gas turbine engine includes a shroud with an abradable section and a non-abradable section that cooperatively define a shroud surface. The gas turbine engine also includes a rotor that is supported for rotation within the shroud to generate an aft axial fluid flow. The rotor includes a blade with a blade tip that is crowned and that opposes the abradable section and the non-abradable section of the shroud surface. A crown area of the blade tip opposes the abradable section. A casing treatment feature is provided in the non-abradable section of the shroud to oppose the blade tip of the rotor.

公开(公告)号：US20200018180A1

公开(公告)日：2020-01-16

申请号：US16564617

申请日：2019-09-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dave Dischinger ,  Nick Nolcheff

IPC: F01D17/02 ,  F01D17/24 ,  F01D17/12

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing particulate at a first position that is located at a first side of a gas turbine engine component and supplying a first sensor signal representative thereof, and sensing particulate at a second position that is located at a second side of the gas turbine engine component and downstream of the first position, and supplying a second sensor signal representative thereof, where the second position. The first sensor and second sensor signals are processed to determine the type, quantity, and size of particulate at the first and second positions, respectively. Based at least on the quantity and size of the particulate at the first and the second positions, an amount of the particulate accumulated on the gas turbine engine component is determined.

公开(公告)号：US10208628B2

公开(公告)日：2019-02-19

申请号：US15085625

申请日：2016-03-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  John Schugardt ,  Nick Nolcheff ,  John Meier ,  Yogendra Yogi Sheoran ,  Shezan Kanjiyani ,  Daniel Aukland

IPC: F01D25/32 ,  F02C7/36 ,  F04D29/42 ,  F04D29/70

Abstract: A turbine engine incorporating a fine particle separation means includes a radial compressor that rotates about a longitudinal axis, a radially-oriented diffuser located downstream and radially outward, with respect to the longitudinal axis, from the radial compressor, and a flow path positioned downstream and radially outward, with respect to the longitudinal axis, from the diffuser, wherein the flow path comprises an outer annular wall and an inner annular wall between which the compressed air flows, and wherein the flow path comprises an arc the redirects the compressed air from flowing in a substantially radial flow direction to a substantially axial flow direction. The turbine engine further includes an extraction slot in the outer annular wall that fluidly connects with a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the outer annular wall at a position downstream axially along the flow path from the arc.

公开(公告)号：US20180347401A1

公开(公告)日：2018-12-06

申请号：US16108907

申请日：2018-08-22

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  Jong Lee

IPC: F01D25/24 ,  F04D29/54 ,  F04D27/02 ,  F01D9/04 ,  F02C9/18

CPC classification number: F01D25/24 ,  F01D9/04 ,  F02C9/18 ,  F04D27/0215 ,  F04D27/023 ,  F04D27/0238 ,  F04D29/545

Abstract: A compressor includes a rotor platform; a rotor blade; and a casing having an inner surface surrounding the tip and spaced radially outwardly from the tip to define a gap. A secondary air flow system includes a bleed inlet configured to remove secondary air flow from the primary air flow; an injection opening disposed in the inner surface of the casing upstream of the bleed inlet; an accessory conduit; and a plenum fluidly coupled to the bleed inlet, the injection opening, and the accessory conduit. The bleed inlet and plenum at least partially define a secondary air flow path such that a first portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the injection opening and a second portion of the secondary air flow is directed in through the bleed inlet, through the plenum, and out through the accessory conduit.

公开(公告)号：US20180298778A1

公开(公告)日：2018-10-18

申请号：US15490029

申请日：2017-04-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dave Dischinger ,  Nick Nolcheff

IPC: F01D17/02 ,  F01D17/24 ,  F01D17/12

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing particulate at a first position that is located at a first side of a gas turbine engine component and supplying a first sensor signal representative thereof, and sensing particulate at a second position that is located at a second side of the gas turbine engine component and downstream of the first position, and supplying a second sensor signal representative thereof, where the second position. The first sensor and second sensor signals are processed to determine the type, quantity, and size of particulate at the first and second positions, respectively. Based at least on the quantity and size of the particulate at the first and the second positions, an amount of the particulate accumulated on the gas turbine engine component is determined.

公开(公告)号：US20160061054A1

公开(公告)日：2016-03-03

申请号：US14475629

申请日：2014-09-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff

IPC: F01D17/12 ,  F02C9/16 ,  F02C3/04

CPC classification number: F01D25/162 ,  F01D9/00 ,  F01D9/02 ,  F01D9/04 ,  F01D9/041 ,  F01D9/06 ,  F01D9/065 ,  F01D25/24 ,  F02C7/04 ,  F02C7/042 ,  F02C9/16 ,  F02K1/002 ,  F02K1/008 ,  F02K1/28 ,  F02K1/30 ,  F02K1/38 ,  F02K1/46 ,  F05D2240/10 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2270/172 ,  F05D2270/173 ,  F05D2270/18 ,  F23R3/26

Abstract: The present disclosure provides systems and apparatuses for use in turbine systems that integrate structural frame elements into a variable-vectoring flow control configuration in order to reduce the weight and length of such turbine systems. In one exemplary embodiment, an apparatus for directing a gas flow includes an annular outer structural casing, an annular central hub disposed within the outer structural casing, and a plurality of structural support elements extending radially between the central hub and the outer structural casing. The apparatus further includes a plurality of positionally-fixed, variable-vectoring flow control bodies extending radially between the central hub and the outer structural casing and positioned circumferentially along the central hub between ones of the plurality of structural support elements.

Abstract translation: 本公开提供了在涡轮机系统中使用的系统和装置，其将结构性框架元件集成到可变向量流控制构型中，以便减小这种涡轮机系统的重量和长度。 在一个示例性实施例中，用于引导气流的装置包括环形外部结构外壳，设置在外部结构外壳内的环形中心毂以及在中心毂和外部结构外壳之间径向延伸的多个结构支撑元件。 该装置还包括多个位置固定的可变向量流量控制体，其径向地延伸在中心轮毂和外部结构壳体之间，并且沿着中心轮毂圆周地定位在多个结构支撑元件之间。

公开(公告)号：US20150030435A1

公开(公告)日：2015-01-29

申请号：US13951592

申请日：2013-07-26

Applicant: Honeywell International Inc.

Inventor： Jeff Howe ,  Nick Nolcheff ,  Harry Lester Kington

IPC: F02C7/05

CPC classification number: F02C7/052 ,  F05D2250/71 ,  F05D2260/16 ,  F05D2270/172

Abstract: An inlet particle separator system for an engine includes a hub section, a shroud section, a splitter, and a plasma flow control actuator. The shroud section surrounds at least a portion of the hub section and is spaced apart therefrom to define a passageway having an air inlet. The splitter is disposed downstream of the air inlet and extends into the passageway to divide the passageway into a scavenge flow path and an engine flow path. The plasma flow control actuator is coupled to the hub section and is disposed between the air inlet and the splitter.

Abstract translation: 用于发动机的入口颗粒分离器系统包括毂部分，护罩部分，分离器和等离子体流动控制致动器。 护罩部分围绕轮毂部分的至少一部分并与其间隔开以限定具有空气入口的通道。 分流器设置在空气入口的下游并延伸到通道中，以将通道分成清流流动路径和发动机流动路径。 等离子体流量控制致动器联接到毂部分并且设置在空气入口和分离器之间。

公开(公告)号：US20140321987A1

公开(公告)日：2014-10-30

申请号：US13843246

申请日：2013-03-15

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  Dan Frias ,  Thomas C. Corke ,  Scott C. Morris

IPC: F01D17/00

CPC classification number: F02C9/16 ,  F01D9/041 ,  F01D17/00 ,  F01D17/12 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2270/172 ,  H05H1/2406 ,  H05H2001/2412 ,  H05H2001/2418

Abstract: A system for directing airflow, a gas turbine engine, and a method for directing airflow exiting a cascade of internal airfoils are provided. An exemplary system for directing airflow includes a cascade of internal structures spanning an airflow path. Each of the internal structures includes a rounded trailing edge. The system further includes at least one plasma generating device positioned on the rounded trailing edge of each internal structure. Also, the system includes a controller configured to selectively energize and de-energize each plasma generating device to selectively alter a direction of local airflow around each internal structure to produce a combined airflow exiting the cascade in a desired direction.

Abstract translation: 提供了用于引导气流的系统，燃气涡轮发动机以及用于引导离开级联的内部翼型件的气流的方法。 用于引导气流的示例性系统包括横跨气流路径的内部结构的级联。 每个内部结构都包括一个圆形的后缘。 该系统还包括位于每个内部结构的圆形后缘上的至少一个等离子体产生装置。 此外，该系统包括控制器，其被配置为选择性地激励和断电每个等离子体产生装置，以选择性地改变围绕每个内部结构的局部气流的方向，以产生沿所需方向离开级联的组合气流。

公开(公告)号：US12196141B2

公开(公告)日：2025-01-14

申请号：US18303111

申请日：2023-04-19

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Nick Nolcheff ,  Ryan Bernaud ,  Greyson Boyll

IPC: F02C9/18 ,  F02C3/08 ,  F02C9/20 ,  F02C9/22 ,  F04D27/02

Abstract: Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.