公开(公告)号：US11015465B2

公开(公告)日：2021-05-25

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 ,  F04D29/68 ,  F04D29/52

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：US11378093B2

公开(公告)日：2022-07-05

申请号：US17060219

申请日：2020-10-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： David Richard Hanson ,  John A. Gunaraj ,  Jeffrey Hayes ,  Nick Nolcheff ,  John Repp

IPC: F01D5/14 ,  F04D29/38 ,  F04D29/32

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. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.

公开(公告)号：US11181120B2

公开(公告)日：2021-11-23

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 ,  F01D5/14

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：US20210207614A1

公开(公告)日：2021-07-08

申请号：US17060219

申请日：2020-10-01

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： David Richard Hanson ,  John A. Gunaraj ,  Jeffrey Hayes ,  Nick Nolcheff ,  John Repp

IPC: F04D29/38 ,  F01D5/14

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. The throat dimension between 90% of the span and the tip of the adjacent ones of the plurality of airfoils has a first value that is less than 70% of the maximum value.

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：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：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.

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：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.