公开(公告)号：US20160252098A1

公开(公告)日：2016-09-01

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: F04D27/00 ,  F04D29/32 ,  F04D29/54 ,  F04D19/02

CPC classification number: F04D29/684 ,  F01D9/065 ,  F04D27/0215 ,  F04D27/0238 ,  F04D29/522 ,  F04D29/682 ,  F05D2270/10 ,  F05D2270/101

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.

Abstract translation: 为压缩机提供了方法和装置。 压缩机包括具有第一转子和第一定子的第一级，以及在流体流动方向上从第一级下游的第二级。 压缩机还包括二次流系统，其将来自第二级的流体引导到第一定子中以改进压缩机的性能和稳定性中的至少一个。

公开(公告)号：US11473438B2

公开(公告)日：2022-10-18

申请号：US16431368

申请日：2019-06-04

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  John Repp ,  Peter Hall

IPC: F01D11/08 ,  F01D25/24 ,  F04D29/52 ,  F01D9/04 ,  F04D27/00

Abstract: Rotor systems and methods for improved performance with extended range to stall fabricated through the use of additive manufacturing. A rotor has blades that extend to tips and rotates about an axis. A casing fits over the rotor so that the tips are configured to pass proximate the casing when the rotor rotates. The casing channels a flow stream across the rotor. Grooves are defined in the casing and extend longitudinally at an acute angle relative to the axis. The grooves extend a distance upstream from a leading edge of the blades and over at least a portion of the blade tips so that the blade tips are configured to pass across the grooves when the rotor rotates.

公开(公告)号：US20210381385A1

公开(公告)日：2021-12-09

申请号：US16892155

申请日：2020-06-03

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Bruce Reynolds ,  John Gunaraj ,  Dawn McNamee

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 extending in a spanwise direction from 0% span at a root to 100% span at a tip and having a leading edge and a trailing edge. The airfoil has a plurality of spanwise locations between the root and the tip each having a normalized local maximum thickness. A value of the normalized local maximum thickness decreases from the root to a minimum value and increases from the minimum value to the tip, and the minimum value is within 60% span to 90% span. The rotor includes a rotor disk coupled to the rotor blade configured to be coupled to a shaft or a fan to rotate with the shaft or the fan, respectively, at the same speed as the shaft and the fan.

公开(公告)号：US20210381382A1

公开(公告)日：2021-12-09

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 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 and the fan.

公开(公告)号：US10859094B2

公开(公告)日：2020-12-08

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: F01D5/14 ,  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.

公开(公告)号：US20200308970A1

公开(公告)日：2020-10-01

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

IPC: F01D9/04

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.

公开(公告)号：US10670040B2

公开(公告)日：2020-06-02

申请号：US15439430

申请日：2017-02-22

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Repp ,  Jeffrey Hayes ,  John A Gunaraj ,  Yoseph Gebre-Giorgis

IPC: F04D29/32 ,  F04D29/54 ,  F04D29/34 ,  F01D5/14 ,  F01D5/34 ,  F02K3/06 ,  F01D5/02 ,  F02C7/05 ,  B64D33/02 ,  B64C11/14

Abstract: Embodiments of a core-protecting fan module are provided, as are embodiments of a turbofan engine containing such a fan module. In an embodiment, the core-protecting fan module contains a nose member, a fan rotor downstream of the nose member, a full span stator downstream of the fan rotor, and a splitter structure downstream of the fan rotor. The fan rotor includes a plurality of fan blades, which extends from a rotor hub and which is angularly spaced about a rotational axis. Certain fundamental angular relationships are observed between the angles formed by rotational axis, the nose member, the fan rotor, and a leading edge of the splitter structure to reduce contaminant ingestion by the core flow path and to promote moisture shedding to reduce susceptibility to icing within the fan module, while further avoiding or minimizing negative impacts to other structural and functional aspects of the turbofan engine.

公开(公告)号：US20200158127A1

公开(公告)日：2020-05-21

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

IPC: F04D29/38

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.

公开(公告)号：US09970452B2

公开(公告)日：2018-05-15

申请号：US14623761

申请日：2015-02-17

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Richard David Conner ,  Michael Todd Barton ,  Yoseph Gebre-Giorgis ,  Harry Lester Kington ,  John Repp

IPC: F04D29/28 ,  F01D5/22 ,  F01D9/04 ,  F04D29/32 ,  F02C3/09

CPC classification number: F04D29/284 ,  F01D5/225 ,  F01D9/04 ,  F02C3/09 ,  F05D2250/38 ,  F05D2260/941 ,  Y02T50/671

Abstract: Embodiments of a forward-swept impeller are provide, as are embodiments of a gas turbine engine containing a forward-swept impeller. In one embodiment, the gas turbine engine includes a shaft and a forward-swept impeller mounted to the shaft. The forward-swept impeller includes, in turn, an inboard impeller section, an outboard impeller section circumscribing the inboard impeller section, and a plurality of hub flow paths extending over the forward-swept impeller from the inboard impeller section to the outboard impeller section. The plurality of hub flow paths each have a flow path exit that is tilted in a forward direction, as taken along a line tangent to the flow path exit.