公开(公告)号：US20200166049A1

公开(公告)日：2020-05-28

申请号：US16201699

申请日：2018-11-27

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：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.

公开(公告)号：US09638103B2

公开(公告)日：2017-05-02

申请号：US13951592

申请日：2013-07-26

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Jeff Howe ,  Nick Nolcheff ,  Harry Lester Kington

IPC: F02C7/052

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.

公开(公告)号：US20170058782A1

公开(公告)日：2017-03-02

申请号：US15340370

申请日：2016-11-01

Applicant: HONEYWELL INTERNATIONAL INC.

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

IPC: F02C9/16 ,  F01D9/04 ,  H05H1/24 ,  F01D17/12

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 method for directing airflow exiting a cascade of internal airfoils includes coupling a first plasma generating device on a first surface and a rounded trailing edge of each of the internal airfoils. The method also includes coupling a second plasma generating device on an opposite second surface and the rounded trailing edge of each of the internal airfoils. Further, the method includes selectively energizing the first plasma generating device and the second plasma generating device on each of the internal airfoils to produce a plasma and to selectively alter a direction of local airflow around each of the internal airfoils 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。 用于引导离开级联的内部翼型件的气流的示例性方法包括将第一等离子体产生装置联接在每个内部翼型件的第一表面和圆形后缘上。 该方法还包括将第二等离子体产生装置耦合在相对的第二表面和每个内部翼型件的圆形后缘上。 此外，该方法包括在每个内部翼型件上选择性地激励第一等离子体产生装置和第二等离子体产生装置以产生等离子体并且选择性地改变围绕每个内部翼型件的局部气流的方向，以产生离开 在期望的方向上级联。