Ihi Corporation

Ishikawajima-Harima Heavy Industries Co., Ltd.

Japan Aerospace Exploration Agency

Chiyuki Nakamata

Yoji Okita

Osamu Watanabe

Shu Fujimoto

Seiji Kubo

Kazuo Yonekura

Kozo Nita

Jun Hosoi

Takahiro Bamba

Takashi Yamane

Nagayoshi Hiromitsu

Yoshitaka Fukuyama

Yuuta Matsumoto

Takeomi Ideta

Atsushi Hirata

The invention is a combustor liner () of a dual wall cooling structure including an inner wall section () configured to surround a combustion region () and in which a plurality of effusion cooling holes () are formed, and an outer wall section () formed to be spaced apart from the inner wall section () and in which a plurality of impingement cooling holes () are formed, wherein the inner wall section () is constituted by a plurality of plate-shaped members (), and a support guide member () is provided which is configured to guide the plurality of plate-shaped members () to enable free insertion and extraction and support the plurality of plate-shaped members () at intervals such that deformation by thermal expansion is able to be absorbed.

Combustor liner with dual wall cooling structure

The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.

Turbine blade

The present invention relates to an impingement cooling mechanism () that ejects a cooling gas (G) toward a cooling target () from a plurality of impingement holes () formed in an opposing member () that is arranged opposite the cooling target (). Turbulent flow promoting portions () are provided in the flow path of a crossflow (CF), which is a flow that is formed by the cooling gas (G) after being ejected from the impingement holes (). The turbulent flow promoting portions () are constituted so that a turbulent flow is promoted from the upstream side to the downstream side of the crossflow (CF).

Impingement cooling mechanism, turbine blade and cumbustor

The present invention relates to an impingement cooling mechanism that ejects a cooling gas toward a cooling target () from a plurality of impingement holes () formed in a facing member () that is disposed facing the cooling target (). Blocking members () that block a crossflow (CF), which is a flow formed by the cooling gas after being ejected from the impingement holes (), are installed on at least the upstream side of the crossflow (CF) with respect to at least a portion of the impingement holes (). Turbulent flow promoting portions () are provided in the flow path (R) of the crossflow (CF) regulated by the blocking members ().

Impingement cooling mechanism, turbine blade and combustor

The present invention is a turbine blade () having a hollow blade body (). This turbine blade () is provided with: cooling air holes () that penetrate the blade body () from an internal wall surface () to an external wall surface () thereof, and are provided with a straight tube portion () that is located on the internal wall surface () side of the blade body (), and an expanded diameter portion () that is located on the external wall surface () side of the blade body (); and with a guide groove () that is located on an internal wall of the expanded diameter portion () and that guides cooling air (Y) in the expanded diameter portion ().

The film cooling structure includes: a wall surface along which a heating medium flows; and at least one pair of film cooling holes that open at the wall surface and that blow a cooling medium. The pair of film cooling holes are arranged to be adjacent to each other in a main flow direction of the heating medium. In addition, perforation directions of the pair of film cooling holes are set such that directions of swirls of the cooling medium formed by blowing are opposite to each other, a swirl of the cooling medium on a downstream side in the main flow direction is mixed and merged with another swirl of the cooling medium on an upstream side in the main flow direction, and the merged cooling medium flows along the wall surface in a direction intersecting with the main flow direction.

Film cooling structure and turbine blade

Disclosed is a turbine blade capable of being cooled by a coolant gas supplied to a hollow region, wherein a plurality of meandering flow paths that guide the coolant gas between the suction wall surface and the pressure wall surface while causing the coolant gas to repeatedly meander are continuously arranged from the hub side toward the tip side of the turbine blade, and the meandering flow paths adjacent to each other cause the coolant gas to meander in different repetitive patterns.

A cooling structure of a turbine airfoil cools a turbine airfoil () exposed to hot gas (), using cooling air () of a temperature lower than that of the hot gas. The turbine airfoil () includes an external surface (), an internal surface () opposite to the external surface, a plurality of film-cooling holes () blowing the cooling air from the internal surface toward the external surface to film-cool the external surface, and a plurality of heat-transfer promoting projections () integrally formed with the internal surface and protruding inwardly from the internal surface. The turbine airfoil further includes a hollow cylindrical insert () which is positioned inside the internal surface of the turbine airfoil and to which the cooling air is supplied. The insert has a plurality of impingement holes () for impingement-cooling the internal surface ().

Cooling structure of turbine airfoil

A cooled turbine rotor blade comprises a blade body having a cooling passage so that cooling air is introduced, and a film cooling hole which is formed on the surface of the blade body and includes an inlet opening and a wedge shaped spurt out opening. The film cooling hole is divided into at least two openings by a partition wall on the outlet side of the film cooling hole.

Growing community of inventors

Tokyo, Japan

Chiyuki Nakamata