Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A heat radiator for an aircraft, which cools a heat source installed in the aircraft, includes a heat radiating part in which a contact surface comes into contact with a main flow, the contact surface being formed with a concave portion or a convex portion in which a surface thereof directed upstream in a flow direction of the main flow is curved in a plan view.

Abstract: The invention is a combustor liner (12) of a dual wall cooling structure including an inner wall section (30) configured to surround a combustion region (13) and in which a plurality of effusion cooling holes (31) are formed, and an outer wall section (20) formed to be spaced apart from the inner wall section (30) and in which a plurality of impingement cooling holes (21) are formed, wherein the inner wall section (30) is constituted by a plurality of plate-shaped members (40), and a support guide member (50) is provided which is configured to guide the plurality of plate-shaped members (40) to enable free insertion and extraction and support the plurality of plate-shaped members (40) at intervals such that deformation by thermal expansion is able to be absorbed.

Abstract: The present disclosure is a heat radiator for an aircraft which cools a heat source installed in the aircraft, which includes a heat radiating part in which a contact surface comes into contact with a main flow, the contact surface being formed with a concave portion or a convex portion in which a surface thereof directed upstream in a flow direction of the main flow is curved in a plan view.

Abstract: A cooling device includes a heat sink that includes a plurality of first heat radiating fins and a plurality of second heat radiating fins, and a compressor as a blower that causes cooling air to flow from an inlet toward an outlet of a cooling passage of the heat sink. The cooling device includes in a flow direction of the cooling air that passes via the heat sink a mist supplier arranged upstream of the heat sink and that supplies mist M to the cooling passage of the heat sink.

Abstract: 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.

Abstract: The present invention relates to an impingement cooling mechanism (1) that ejects a cooling gas (G) toward a cooling target (2) from a plurality of impingement holes (4) formed in an opposing member (3) that is arranged opposite the cooling target (2). Turbulent flow promoting portions (6) 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 (4). The turbulent flow promoting portions (6) are constituted so that a turbulent flow is promoted from the upstream side to the downstream side of the crossflow (CF).

Abstract: A cooling device includes a heat sink that includes a plurality of first heat radiating fins and a plurality of second heat radiating fins, and a compressor as a blower that causes cooling air to flow from an inlet toward an outlet of a cooling passage of the heat sink. The cooling device includes in a flow direction of the cooling air that passes via the heat sink a mist supplier arranged upstream of the heat sink and that supplies mist M to the cooling passage of the heat sink.

Abstract: The invention is a combustor liner (12) of a dual wall cooling structure including an inner wall section (30) configured to surround a combustion region (13) and in which a plurality of effusion cooling holes (31) are formed, and an outer wall section (20) formed to be spaced apart from the inner wall section (30) and in which a plurality of impingement cooling holes (21) are formed, wherein the inner wall section (30) is constituted by a plurality of plate-shaped members (40), and a support guide member (50) is provided which is configured to guide the plurality of plate-shaped members (40) to enable free insertion and extraction and support the plurality of plate-shaped members (40) at intervals such that deformation by thermal expansion is able to be absorbed.

Abstract: A turbine blade has hollowness, and is provided with a back-side wall of which a portion of the inner wall surface is exposed at the rear edge portion, with cooling air flown along the inner wall surface at the exposed region; and a recess provided in the inner wall surface at the exposed region. The contour of the recess (5) viewed from the normal direction of the inner wall surface of the back-side wall is set to a shape that is symmetrical centered on a reference axis (L) that intersects the flow direction of cooling air, and that broadens along the reference axis (L).

Abstract: The present invention relates to an impingement cooling mechanism that ejects a cooling gas toward a cooling target (2) from a plurality of impingement holes (3b) formed in a facing member (3) that is disposed facing the cooling target (2). Blocking members (5) that block a crossflow (CF), which is a flow formed by the cooling gas after being ejected from the impingement holes (3b), are installed on at least the upstream side of the crossflow (CF) with respect to at least a portion of the impingement holes (3b). Turbulent flow promoting portions (6) are provided in the flow path (R) of the crossflow (CF) regulated by the blocking members (5).

Abstract: The present invention is a turbine blade (1) having a hollow blade body (2). This turbine blade (1) is provided with: cooling air holes (5) that penetrate the blade body (2) from an internal wall surface (2e) to an external wall surface (2f) thereof, and are provided with a straight tube portion (5a) that is located on the internal wall surface (2e) side of the blade body (2), and an expanded diameter portion (5b) that is located on the external wall surface (2f) side of the blade body (2); and with a guide groove (6) that is located on an internal wall of the expanded diameter portion (5b) and that guides cooling air (Y) in the expanded diameter portion (5).

Abstract: The gas turbine engine (S1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided. The flow path surface (31) includes: depression portions (31a) depressed relative to the base surface (32), each depression portion (31a) including at least an area overlapping with a front end (7b1) of each turbine blade (7b), when viewed from a direction of the turbine axis (L); and protrusion portions (31b) protruding relative to the base surface (32), each protrusion portion (31b) being at least part of each area positioned between front ends (7b1) of the turbine blades (7b), when viewed from the above direction.

Abstract: 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.

Abstract: A cooling promoting structure in which a first flow path walls includes a first collision surface which collides with cooling gas flowing through a first flow path, a second flow path walls includes a second collision surface which collides with the cooling gas flowing through a second flow path, and the first flow path and the second flow path are connected to each other via inflow openings at a location where the first collision surface and the second collision surface are disposed.

Abstract: The present invention relates to an impingement cooling mechanism (1) that ejects a cooling gas (G) toward a cooling target (2) from a plurality of impingement holes (4) formed in an opposing member (3) that is arranged opposite the cooling target (2). Turbulent flow promoting portions (6) 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 (4). The turbulent flow promoting portions (6) are constituted so that a turbulent flow is promoted from the upstream side to the downstream side of the crossflow (CF).

Abstract: 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.