Kawasaki Jukogyo Kabushiki Kaisha

B&b Agema Gmbh

Ryozo Tanaka

Takao Sugimoto

Karsten Kusterer

Dieter Bohn

Tomoki Taniguchi

Masahide Kazari

Ryoji Tamai

Yoshihiko Mutou

Kazuhiko Tanimura

Yoshichika Sato

Hirotaka Kurashima

Toshiyuki Yamamoto

Yoshinobu Sakano

Takeshi Horiuchi

Gang Lin

Nurettin Tekin

Anas Elyas

Hiroshi Morishita

Rene Braun

Koichiro Tsuji

Hirokazu Matsuda

Hiromitsu Arai

A gas turbine engine includes a cooling air supply passage that feeds air from a compressor, as a cooling medium, to a turbine by swirling the air in a circumferential direction. The cooling air supply passage includes an entry zone to which the air enters, and a swirl zone in which the air flowing past the entry zone is circumferentially redirected. The gas turbine engine also includes a chamber branching from the swirl zone to capture foreign particles in the air. The chamber is formed to meet the relation: α≥β where, when viewed in a radial direction, α is an angle defined by the swirl zone relative to a horizontal direction and β is an angle defined between the chamber and the swirl zone.

Gas turbine engine

Provided is a rotor blade configured to be implanted in a disc of a rotating body, the rotor blade including a blade root, wherein in a cross-sectional shape of the blade root, the blade root includes at least one stage of protruding parts protruding toward opposite sides with respect to a direction containing a circumferential component, the protruding parts being configured to lock the blade root to the disc, each of the protruding parts has a contact surface configured to come into contact with the disc and inclined so as to extend toward a center part of the blade root from radially inside to radially outside, and each of the protruding parts has a non-contact surface configured not to come into contact with the disc and inclined so as to extend toward the center part of the blade root from the radially inside to the radially outside.

Rotor blade and disc of rotating body

A rotating body includes a rotating body core, and a plurality of blades provided at an outer or inner circumference of the rotating body core at equal intervals in a circumferential direction, and connected circumferentially via an annular connection portion provided separately from the rotating body core. A resonance frequency under a two nodal diameter number mode of the rotating body is lower than or equal to a rotational secondary harmonic frequency with respect to a rated rotation speed. Where Nrepresents an order of a maximum mistuned component among order components of circumferential distribution of mass, rigidity or natural frequency of the blades, arrangement of the blades satisfies N&#x2265;5, and has order components each having ratio less than 1/2, in which the ratio is obtained by dividing the order component by the magnitude of the component of the order N.

Rotating body provided with blades

In a structure for internally cooling a turbine blade, a cooling medium passage is provided in the turbine blade. The cooling medium passage has a shape in which a plurality of cylindrical spaces, each having substantially cylindrical shape, extending in parallel with each other partially overlap each other. A cooling medium supply passage that supplies a cooling medium to the cooling medium passage is connected to a portion of the cooling medium passage that includes a peripheral wall, in a direction that forms an acute angle with respect to a longitudinal direction of the cooling medium passage.

Turbine blade cooling structure

A double-jet film cooling structure includes: an injection port, formed on a wall surface facing a high-temperature gas passage; a main passage as a straight round hole to supply cooling medium to the injection port; a pair of branch passages as straight round holes; and communication passages connecting the main passage to the branch passages. The main passage and the branch passages have same constant inner diameters. Each communication passages has an envelope surface obtained by continuously arranging straight round holes each passing a branch point and having the constant inner diameter. Transverse injection angles of the branch passages relative to gas flow along the wall surface are oriented in opposite directions. An angle between axial direction of the main passage and the wall surface is greater than an angle formed between axial direction of branch passage and the wall surface.

Double-jet film cooling structure and method for manufacturing same

Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.

Double-jet type film cooling structure

At least one sealing arrangement is provided for a connecting mechanism between an inner annular member or an outer annular member and an associated segment to connect between the annular members and the segments. The sealing arrangement includes an elastic sealing member provided between the sealing surfaces, disposed linearly along a side of polygon defined around a central axis.

Sealing arrangement and gas turbine engine with the sealing arrangement

A combined-type gas turbine engine system is provided which achieves high efficiency by very effectively using exhaust heat from a gas turbine engine. In a gas turbine engine system including: a compressor for compressing a first working medium; a heater for heating the compressed first working medium by an external heat source; a turbine for outputting power from the first working medium; an intermediate cooler provided at the compressor for cooling the first working medium compressed by a low-pressure compression part of the compressor and supplying the first working medium to a high-pressure compression part of the compressor; and an exhaust heat boiler using as a heating medium an exhaust gas from the turbine, a Rankine cycle engine using the intermediate cooler and the exhaust heat boiler as heat sources and a cooling medium of the intermediate cooler as a second working medium.

Gas turbine engine system equipped with Rankine cycle engine

A seal mechanism is provided which comprises a structure capable of accommodating radial expansions of turbine rotor without increasing an axial size thereof and providing a reliable sealing property for the turbine rotor for a long time. The seal mechanism comprises a labyrinth sealdefined by a projectionprovided on the turbine rotorB, an outer memberprovided radially outward of the projection and supported for displacement in a radial direction, and an inner memberprovided radially inward of the projection and supported for displacement in the radial direction. A thermal expansion rate of the inner member is greater than that of the outer member.

Seal mechanism for use with turbine rotor

A film cooling structure includes a wall surface which faces a gas-flow passage for high-temperature gas. One or more than one pair of jetting holes are formed on the wall surface so as to respectively jet cooling media into the gas-flow passage. The pair of jetting holes respectively have jetting directions in which the cooling media are jetted from the pair of jetting holes into the gas-flow passage. The jetting directions of the pair of jetting holes are respectively set so as to respectively form swirls in directions in which the cooling media are mutually pressed against the wall surface.

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Kakogawa, Japan

Ryozo Tanaka