Ihi Corporation

Japan Aerospace Exploration Agency

Shu Fujimoto

Yoji Okita

Chiyuki Nakamata

Hitoshi Hattori

Masahiro Matsushita

Takashi Yamane

Seiji Kubo

Yoshitaka Fukuyama

Toyoaki Yoshida

Ryo Ikehara

Youji Ohkita

The film cooling structure includes a wall part extending forward and rearward, and a cooling hole including a tubular inner peripheral surface and inclined such that an outlet is positioned rearward of an inlet. The cooling hole includes a throat having a minimum cross section, and a diffuser part extending from the throat to the outlet. The diffuser part includes a channel cross section expanding rearward and along the wall part as it approaches the outlet. The inner peripheral surface of the cooling hole includes a flat portion extending in a direction perpendicular to the cooling hole and along the wall part at a front part of the inner peripheral surface, and a convex portion projecting from a rear part of the inner peripheral surface toward the flat portion, extending in parallel with the flat portion, and forming the throat between the flat portion and the convex portion.

Film cooling structure and turbine blade for gas turbine engine

The film cooling structure includes a wall part and a cooling hole inclined such that an outlet is positioned rearward of an inlet. The cooling hole includes a straight-tube part and a diffuser part. The diffuser part includes a flat surface, a curved surface curved rearward and forming, together with the flat surface, a semicircular or semi-elliptical channel cross section larger than that of the straight-tube part, a first section and a second section extending from the first section toward the outlet. In the first section, an area of the channel cross section increases as it approaches the outlet. In the second section, the area of the channel cross section increases as it approaches the outlet at an increase rate smaller than that of the first section or is constant. The diffuser part has a width equal to or twice greater than the depth of the diffuser part.

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

A turbine blade that is used in a turbine of a gas turbine engine and cooled by cooling air, and includes a cooling channel that is formed within the turbine blade and in which the cooling air flows, plural bottomed recesses that are formed on a blade surface of the turbine blade and of which each downstream-side inner wall is inclined, and an ejection hole that is formed on each bottom of the plural bottomed recesses and communicates with the cooling channel to eject the cooling air. The ejection hole is formed so that a central line of the ejection hole extends along the downstream-side inner wall. The above turbine blade can improve cooling without reducing efficiency.

Turbine blade and engine component

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.

Turbine blade

In this cooling structure, a cooling flow path, which is meandering around a flow direction of a high temperature combustion gas, is provided in a structural body. The cooling flow path has an inflow path for a cooling air formed inside of the structural body; at least one straight flow path provided with intervals with respect to an axial line; and a turning flow path for communicating the end portions of the inflow path with the straight flow path or communicating with the end portions of the straight flow paths one after another.

Cooling structure

An impingement cooled structure includes a plurality of shroud members disposed in a circumferential direction to constitute a ring-shaped shroud surrounding a hot gas stream, and a shroud cover mounted on radial outside faces of the shroud members to form a cavity therebetween. The shroud cover has a first impingement cooling hole which communicates with the cavity and allows cooling air to be jetted to an inside thereof so as to cool an inner surface of the cavity by impingement. The shroud members each has a hole fin. The hole fin divides the cavity into a plurality of sub-cavities. Further, the hole fin has a second impingement cooling hole which allows the cooling air having flowed through the first impingement cooling hole to be jetted obliquely toward a bottom surface of the sub-cavity adjacent thereto.

Growing community of inventors

Tokyo, Japan

Shu Fujimoto