公开(公告)号：US11131210B2

公开(公告)日：2021-09-28

申请号：US16246902

申请日：2019-01-14

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shraman Narayan Goswami ,  Hasham Hamzamiyan Chougule ,  Jyotichandra Shivaji Roa Jingade ,  Mohd Abdullah Qizar

IPC: F01D17/14 ,  F01D17/18

Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.

公开(公告)号：US20200224549A1

公开(公告)日：2020-07-16

申请号：US16246902

申请日：2019-01-14

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Shraman Narayan Goswami ,  Hasham Hamzamiyan Chougule ,  Jyotichandra Shivaji Roa Jingade ,  Mohd Abdullah Qizar

IPC: F01D17/14 ,  F01D17/18

Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.

公开(公告)号：US20140215998A1

公开(公告)日：2014-08-07

申请号：US13662287

申请日：2012-10-26

Applicant: Honeywell International Inc.

Inventor： Shraman Narayan Goswami ,  Yathiraj Kasal

IPC: F04D29/38

CPC classification number: F04D29/384 ,  F01D5/145 ,  F04D27/023 ,  F04D27/0238 ,  F04D29/324 ,  F04D29/682 ,  F04D29/684 ,  Y02T50/673

Abstract: A rotor blade for a compressor includes a pressure sidewall; a suction sidewall coupled to the pressure sidewall at a leading edge and a trailing edge; and a through hole extending between the pressure sidewall and the suction sidewall.

Abstract translation: 用于压缩机的转子叶片包括压力侧壁; 在前缘和后缘处耦合到压力侧壁的抽吸侧壁; 以及在压力侧壁和吸力侧壁之间延伸的通孔。