Kawasaki Jukogyo Kabushiki Kaisha

Makoto Gouda

Masahiro Ogata

Yoshihiro Yamasaki

Yasufumi Hosokawa

Yuji Matsuzaki

Tomoaki Ikegaya

Katsumi Ikeda

Daisuke Hayashi

Kei Shimada

An axial flow compressor blade unit including a platform section and an airfoil section, which are used as arranged on a circumference about an axis of the compressor. The platform section includes an inner diametric surface segment inwardly of the circumference, an outer diametric surface segment outwardly of the circumference, two annular side surface segments extending in a circumferential direction, two axially side surface segments extending in the axial direction, and a coupling portion formed in each of the annular side surface segments so as to extend in the circumferential direction and being of a shape projecting or recessed in the axial direction. The airfoil section is formed to erect from the platform section so as to extend in a radial direction. The platform section and the airfoil section are formed integrally with each other while having a powdered metal sintered structure.

Blades for axial flow compressor and method for manufacturing same

A sealing member has a first portion. The first portion has a central axis, a first peripheral surface extending in a direction parallel to the central axis, and a central aperture. A first wall portion of a groove has a recess communicated with the first opening of the first channel. The recess has a second peripheral surface complementary to the first peripheral surface of the first portion of the sealing member. The first portion of the sealing member moves radially toward and away from the rotational axis as the first peripheral surface of the sealing member defines and maintains a first sealing contact with the second peripheral surface of the recess. The sealing member moves radially outwardly and thereby makes a second sealing contact surrounding the second opening of the second channel to establish a communication between the first and second openings.

Sealing arrangement for use with gas turbine engine

A gas turbine engine includes: an air flow control system installed in an air intake path for introducing air to a compressor. The air intake path is located outside and upstream with respect to the compressor. The engine also includes intake air flow control means for controlling an intake air flow by operating the air flow control system according to a load of the engine so as to maintain an air-to-fuel ratio in the combustor within a proper range suited to suppress a discharge of an atmospheric pollutant.

Gas turbine engine with intake air flow control mechanism

Growing community of inventors

Himeji, Japan

Makoto Gouda