公开(公告)号：US20200182259A1

公开(公告)日：2020-06-11

申请号：US16732507

申请日：2020-01-02

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Timothy Gentry ,  Bruce David Reynolds ,  Nick Nolcheff

IPC: F04D29/52 ,  F04D29/32 ,  F04D29/16 ,  F01D5/20 ,  F01D11/12

Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord positon within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.

公开(公告)号：US10648484B2

公开(公告)日：2020-05-12

申请号：US15431890

申请日：2017-02-14

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Timothy Gentry ,  Bruce David Reynolds ,  Nick Nolcheff

IPC: F04D29/52 ,  F04D29/16 ,  F04D29/32 ,  F04D29/68 ,  F01D11/08 ,  F02C3/04

Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.

公开(公告)号：US10527060B2

公开(公告)日：2020-01-07

申请号：US15685038

申请日：2017-08-24

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  Timothy Gentry ,  Richard David Conner

IPC: F01D11/00 ,  F01D17/16 ,  F01D5/14 ,  F04D29/54 ,  F04D29/56

Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.

公开(公告)号：US10046424B2

公开(公告)日：2018-08-14

申请号：US14471253

申请日：2014-08-28

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  John A. Gunaraj ,  Timothy Gentry

IPC: B23P15/04 ,  F01D5/14 ,  F01D5/28 ,  F04D29/16 ,  F04D29/32 ,  F04D29/68 ,  F04D29/52

Abstract: Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component.

公开(公告)号：US20180216632A1

公开(公告)日：2018-08-02

申请号：US15420717

申请日：2017-01-31

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Richard David Conner ,  Bruce David Reynolds ,  Timothy Gentry ,  Peter Hall

IPC: F04D29/56 ,  F04D29/54 ,  F04D29/02 ,  F04D27/00 ,  F01D9/04

CPC classification number: F04D29/563 ,  F01D9/041 ,  F01D11/005 ,  F01D17/162 ,  F04D27/002 ,  F04D29/023 ,  F04D29/542 ,  F04D29/644 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/122

Abstract: Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance.

公开(公告)号：US20160059365A1

公开(公告)日：2016-03-03

申请号：US14471253

申请日：2014-08-28

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Bruce David Reynolds ,  John A. Gunaraj ,  Timothy Gentry

IPC: B23P15/04 ,  F01D5/28 ,  F01D5/14

CPC classification number: B23P15/04 ,  F01D5/141 ,  F01D5/145 ,  F01D5/288 ,  F04D29/164 ,  F04D29/324 ,  F04D29/526 ,  F04D29/685 ,  F05D2220/36 ,  F05D2240/307 ,  F05D2250/294 ,  F05D2250/38 ,  Y02T50/673

Abstract: Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component.

Abstract translation: 提供了用于改进燃气涡轮发动机的性能的方法，其包括具有安装在转子壳体中并具有转子叶片的转子的部件。 尖端扫掠被施加到一个或多个转子叶片的前缘，每个叶片具有压力侧壁和沿径向方向延伸的根部和尖端之间的周向相对的吸力侧壁，并且在轴向方向上在前缘和后缘之间 。 调整一个或多个刀片几何设计参数。 转子壳体处理在一个或多个转子叶片中的至少一个上被施加到转子壳体上。 施加和调节步骤在转子的设计期间进行，并且使得测量的失速余量与组件的效率的提高基本上匹配所需的失速裕度。