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：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：US20210079929A1

公开(公告)日：2021-03-18

申请号：US16951258

申请日：2020-11-18

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  Nick Nolcheff ,  Cristopher Frost

IPC: F04D29/44

Abstract: High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.

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：US10738692B2

公开(公告)日：2020-08-11

申请号：US15709541

申请日：2017-09-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Nick Nolcheff ,  John Meier ,  James Laffan ,  Alan D. Hemmingson ,  Cristian Anghel ,  Mike Koerner

IPC: F02B43/08 ,  F02B77/14 ,  F02B43/00 ,  H02K9/04 ,  B60R16/03 ,  H02K9/16 ,  H02K7/18 ,  F02C6/00 ,  F02K5/00 ,  B64D27/24

Abstract: A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

公开(公告)号：US20200248712A1

公开(公告)日：2020-08-06

申请号：US16266484

申请日：2019-02-04

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  Nick Nolcheff ,  Cristopher Frost

IPC: F04D29/44 ,  F04D29/22

Abstract: Circumferentially-split diffuser assemblies utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the diffuser assembly includes flow passages, which extend through the diffuser assembly and which include diffuser flow passage sections. Diffuser airfoils are interspersed with the diffuser flow passage sections. The diffuser airfoils include inboard and outboard airfoil segments distributed around a diffuser assembly centerline. The inboard and outboard airfoil segments are contained in and, thus, defined by inner and outer annular diffuser structures, respectively. The outer annular diffuser structure circumscribes the inner annular diffuser structure. In certain cases, the inboard airfoil segments and at least a portion of inner annular diffuser structure are composed of a first material, while the outboard airfoil segments and at least a portion of outboard annular diffuser structure are composed of a second material different than the first material.

公开(公告)号：US20200224550A1

公开(公告)日：2020-07-16

申请号：US16834112

申请日：2020-03-30

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Dave Dischinger ,  Nick Nolcheff

IPC: F01D21/00 ,  F01D17/02

Abstract: A system and method for determining particulate accumulation in a gas turbine engine includes sensing the number, size, and type of particulate at a first position on the gas turbine engine and supplying first data representative thereof, where the first position located at a first side of a gas turbine engine component; sensing the number, size, and type of particulate at a second position on the gas turbine engine and supplying first data representative thereof, where the second position located at a second side of the gas turbine engine component and downstream of the first position; and processing the first data and the second data to determine the mass of the particulate accumulated on the gas turbine engine component.

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.