公开(公告)号：US20190003487A1

公开(公告)日：2019-01-03

申请号：US16013322

申请日：2018-06-20

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Koji TERAUCHI ,  Daisuke UEMURA ,  Hiroshi KUBO ,  Naoto SAKAI ,  Toshimasa MIURA ,  Yuki ISHITOBI

IPC: F04D29/54 ,  F01D9/04 ,  F23R3/10 ,  F23R3/46

Abstract: A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.

公开(公告)号：US20180298917A1

公开(公告)日：2018-10-18

申请号：US16013042

申请日：2018-06-20

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Koji TERAUCHI ,  Daisuke UEMURA ,  Hiroshi KUBO ,  Naoto SAKAI ,  Toshimasa MIURA ,  Yuki ISHITOBI

IPC: F04D29/54 ,  F23R3/46 ,  F02C3/04

CPC classification number: F04D29/541 ,  F02C3/04 ,  F04D29/544 ,  F05D2220/32 ,  F05D2220/3219 ,  F05D2240/126 ,  F05D2240/128 ,  F05D2240/35 ,  F23R3/04 ,  F23R3/46

Abstract: A gas turbine engine, in which a compressed gas from a compressor of an axial-flow type is burned in a combustor and an obtained combustion gas drives a turbine, includes: a diffuser of an annular shape connected to an outlet of the compressor, the diffuser including a diffuser inner tube and a diffuser outer tube that are tubular members disposed concentrically with each other; and a plurality of partition members that are disposed in a diffuser flow path, which is an annular space formed between the diffuser inner tube and the diffuser outer tube, and divide the diffuser flow path in a circumferential direction.

公开(公告)号：US20180298918A1

公开(公告)日：2018-10-18

申请号：US16013396

申请日：2018-06-20

Applicant: KAWASAKI JUKOGYO KABUSHIKI KAISHA

Inventor： Koji TERAUCHI ,  Daisuke UEMURA ,  Hiroshi KUBO ,  Naoto SAKAI ,  Toshimasa MIURA ,  Yuki ISHITOBI

IPC: F04D29/54 ,  F02C7/28 ,  F23R3/46 ,  F01D9/02 ,  F23R3/04

Abstract: A gas turbine engine includes: a plurality of combustors disposed so as to incline radially outward from a turbine side toward a compressor side; and a diffuser inner tube and outer tube forming a diffuser as an upstream portion of a path that introduces a compressed gas from the compressor to the combustors. A transition duct portion of each combustor has such a shape that a circumferential dimension thereof gradually decreases from the turbine side to the compressor side so that a circumferential gap is formed between the transition duct portions. Downstream-side portions of the diffuser inner tube and outer tube each have a shape gradually increasing in diameter toward the downstream side. A turbine-side end of the circumferential gap at an inner diameter side of the transition duct portion is positioned radially inward of an imaginary extension conical surface continuous from the diffuser inner tube.