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：US20180238341A1

公开(公告)日：2018-08-23

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 ,  F02K3/06

CPC classification number: F04D29/325 ,  B64C11/14 ,  B64D33/02 ,  B64D2033/0233 ,  F01D5/021 ,  F01D5/141 ,  F01D5/34 ,  F02C7/05 ,  F02K3/06 ,  F04D29/34 ,  F04D29/541 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/20 ,  Y02T50/671 ,  Y02T50/673

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：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：US11280199B2

公开(公告)日：2022-03-22

申请号：US16198260

申请日：2018-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael R. McNamee ,  Nick Nolcheff ,  Yoseph Gebre-Giorgis ,  John A. Gunaraj ,  Jeffrey Hayes ,  Constantinos Vogiatzis

IPC: F01D5/14 ,  F01D5/02

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil. 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 a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value, decreases from the first position value to a second position value and increases from the second position value to the tip. The first position value is at a spanwise location within 20% to 50% of the span.

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：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：US20200157941A1

公开(公告)日：2020-05-21

申请号：US16198260

申请日：2018-11-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Michael R. McNamee ,  Nick Nolcheff ,  Yoseph Gebre-Giorgis ,  John A. Gunaraj ,  Jeffrey Hayes ,  Constantinos Vogiatzis

IPC: F01D5/14 ,  F01D5/02

Abstract: A rotor blade for a compressor of a gas turbine engine includes an airfoil. 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 a leading edge to a trailing edge. The airfoil has a location of local maximum thickness defined as a ratio of a first arc distance along the mean camber line between the leading edge and a position of the local maximum thickness to a total arc distance along the mean camber line from the leading edge to the trailing edge. A value of the ratio increases from the root to a first position value, decreases from the first position value to a second position value and increases from the second position value to the tip. The first position value is at a spanwise location within 20% to 50% of the span.