公开(公告)号：US12006879B1

公开(公告)日：2024-06-11

申请号：US18170161

申请日：2023-02-16

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shakeel Nasir ,  John McClintic ,  Jeffrey Krise

IPC: F02C9/18

CPC classification number: F02C9/18 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/60

Abstract: A bleed arrangement for a turbomachine that results in uniform flow to the combustor. A turbomachine includes a compressor, a combustor disposed to receive the compressed air from the compressor through a flow path, and a diffuser disposed in the flow path between the compressor and the combustor. A number of bleed holes are disposed downstream in the flow path from the diffuser and are configured to direct bleed air compressed by the compressor away from the combustor. The number of bleed holes have a plural number of sizes configured to provide uniform compressor exit flow distribution around a circumference of the diffuser.

公开(公告)号：US11506060B1

公开(公告)日：2022-11-22

申请号：US17305828

申请日：2021-07-15

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul Kurlak ,  Ardeshir Riahi ,  Benjamin D. Kamrath ,  Jason Smoke ,  John McClintic

IPC: F01D11/00 ,  F01D5/20 ,  F01D5/06 ,  F01D5/14

Abstract: A radial turbine rotor associated with an engine includes a disk, and a plurality of blades spaced apart about a perimeter of the disk. Each blade includes a forward end, an aft end and a root. The radial turbine rotor includes a plurality of sectors, with each sector coupled to the root of a respective blade of the plurality of blades. Each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, and each sector of the plurality of sectors defines at least one pocket between the first surface and the second surface proximate the forward end that extends toward the aft end. The radial turbine rotor includes a feather seal slot defined between adjacent sectors of the plurality of sectors proximate the first surface.