Kawasaki Jukogyo Kabushiki Kaisha

Daisuke Uemura

Koji Terauchi

Naoto Sakai

Hiroshi Kubo

Toshimasa Miura

Yuki Ishitobi

Takuya Ikeguchi

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.

Gas turbine engine with diffuser having an annular dividing guide body

Provided is a structure for bleeding gas from a chamber for receiving compressed gas from a compressor of a gas turbine engine and supplying the compressed gas to a combustor. The structure includes: a turbine casing covering an outer circumference of a turbine; an engine housing forming, between the engine housing and the turbine casing, a bleeding space that communicates with the chamber; a bleeding duct through which compressed gas in the bleeding space is guided to the outside of the engine housing; and an annular partitioning member arranged on an upstream side, relative to the bleeding duct in the bleeding space so as to separate the bleeding space from the chamber, and having a plurality of communication holes through which an upstream side and a downstream side relative to the partitioning member communicate with each other.

Bleeding structure for gas turbine engine

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.

Gas turbine engine

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.

Growing community of inventors

Kobe, Japan

Daisuke Uemura