Abstract: An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

Abstract: A thrust increasing device includes: a fuel injector that ejects fuel toward a jet flow; an ignition device that is disposed downstream from the fuel injector; a cylindrical duct that surrounds a combustion region; a flame holder that is disposed in the duct; and a swirling flow generating part that maintains an axial flow of the jet flow in an axial direction of the duct in an outer region of the duct in a radial direction inside the duct and that converts the jet flow to a swirling flow centered on an axis of the duct in an inner region of the duct in the radial direction inside the duct.

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 embodiment improves the durability of an afterburner and yet suppresses a reduction in the engine efficiency of an aircraft engine. A ring-shaped cooling channel through which cooling air flows is formed between the outer peripheral surface of a liner and the inner peripheral surface of a rear duct. A plurality of cooling holes for blowing the cooling air along the inner peripheral surface of the liner are formed penetrating the liner. A ring-shaped annulus flame-holding member on the inner peripheral surface of the liner is provided concentrically with respect to a plurality of radial flame-holding members. The inner diameter of the annulus flame-holding member decreases in the downstream direction. The annulus flame-holding member functions as a throttle ring which throttles the flowing of a main flow of a mixed gas inside the liner.

Abstract: The present embodiment sufficiently ensures the ignition stability and the flame-holding property of an afterburner while suppressing a reduction in the efficiency of an aircraft engine. A flame holder is disposed directly downstream of an injection hole of a fuel injector in a liner. The flame holder comprises: a ring-shaped annulus flame-holding member which is provided on the inner circumferential surface of the liner and is capable of propagating a flame in the circumferential direction; and a plurality of radial flame-holding members which are radially disposed inwards of the annulus flame-holding member and are capable of propagating the flame in the radial direction. A guide ring is provided inwards of the radial flame-holding members, and a ring-shaped guide channel that guides a fuel-containing mixed gas in the downstream direction is formed between the outer peripheral surface of the guide ring and the inner peripheral surface of the annulus flame-holding member.

Abstract: An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

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 embodiment improves the durability of an afterburner and yet suppresses a reduction in the engine efficiency of an aircraft engine. A ring-shaped cooling channel through which cooling air flows is formed between the outer peripheral surface of a liner and the inner peripheral surface of a rear duct. A plurality of cooling holes for blowing the cooling air along the inner peripheral surface of the liner are formed penetrating the liner. A ring-shaped annulus flame-holding member on the inner peripheral surface of the liner is provided concentrically with respect to a plurality of radial flame-holding members. The inner diameter of the annulus flame-holding member decreases in the downstream direction. The annulus flame-holding member functions as a throttle ring which throttles the flowing of a main flow of a mixed gas inside the liner.

Abstract: A thrust increasing device includes: a fuel injector that ejects fuel toward a jet flow; an ignition device that is disposed downstream from the fuel injector; a cylindrical duct that surrounds a combustion region; a flame holder that is disposed in the duct; and a swirling flow generating part that maintains an axial flow of the jet flow in an axial direction of the duct in an outer region of the duct in a radial direction inside the duct and that converts the jet flow to a swirling flow centered on an axis of the duct in an inner region of the duct in the radial direction inside the duct.

Abstract: The present embodiment sufficiently ensures the ignition stability and the flame-holding property of an afterburner while suppressing a reduction in the efficiency of an aircraft engine. A flame holder is disposed directly downstream of an injection hole of a fuel injector in a liner. The flame holder comprises: a ring-shaped annulus flame-holding member which is provided on the inner circumferential surface of the liner and is capable of propagating a flame in the circumferential direction; and a plurality of radial flame-holding members which are radially disposed inwards of the annulus flame-holding member and are capable of propagating the flame in the radial direction. A guide ring is provided inwards of the radial flame-holding members, and a ring-shaped guide channel that guides a fuel-containing mixed gas in the downstream direction is formed between the outer peripheral surface of the guide ring and the inner peripheral surface of the annulus flame-holding member.

Abstract: An aircraft engine includes an afterburner which has a flame stabilizer. The flame stabilizer maintains a flame generated from a mixed gas of a combustion gas and air. The flame stabilizer includes multiple gutters each configured to generate a flame stabilization area for the flame on its downstream side. Each gutter is formed from: a curved apex section having a stagnation point; and flat plate-shaped side surface sections integrally formed on the respective two sides of the apex section. Each gutter has a V-shaped cross-sectional shape which is opened to the downstream side. At least one through-hole is formed only in each side surface section of each gutter.

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 combustor for gas turbine engine, wherein: a plurality of impingement-cooling holes are opened passing through an external wall of a liner for cooling air to blow out towards the outer surface of an internal wall of the liner; a plurality of pin-fins are formed on the outer surface of the internal wall of the liner; a plurality of effusion cooling holes are opened passing through the internal wall of the liner for cooling air to blow out along the inner surface of the internal wall of the liner. The top surface of each pin-fin is not in contact with the inner surface of the external wall of the liner and the ratio of the height of the pin-fin to the equivalent diameter of the impingement-cooling hole is set to be 1.0-3.0.

Abstract: A burner 1 for combustion chamber is provided with a cylindrical mixing portion 3 that mixes air for combustion (oxidizing agent) and fuel in the interior thereof and has one end 3a that opens to a combustion portion 2; a spray nozzle (fuel spraying portion) 5 that sprays fuel in the mixing portion 3, being disposed on another end 3b of the mixing portion 3; first blowing ports 6 that introduce the air for combustion to the mixing portion 3 to form a swirling flow with the fuel, being disposed to open to the inner wall of the mixing portion 3; and second blowing ports 7 that additionally introduce the air for combustion to the mixing portion 3, opening in a direction different from the first blowing ports 6 and being disposed further to the other end 3b side of the mixing portion 3 than the swirling flow.

Abstract: A fuel injection valve is provided with a cylindrical injection valve main body in which one end is closed, and a fuel nozzle arranged on a center line of the main body and injecting a fuel. The main body has a plurality of air injection ports for injecting an air to an inner side in a tangential direction and forming a whirl flow in an inner portion in a circumferential direction of a cylinder portion of the main body, and the fuel nozzle has a fuel injection port injecting the fuel toward an inner peripheral surface of the main body.

Abstract: A burner 1 for combustion chamber is provided with a cylindrical mixing portion 3 that mixes air for combustion (oxidizing agent) and fuel in the interior thereof and has one end 3a that opens to a combustion portion 2; a spray nozzle (fuel spraying portion) 5 that sprays fuel in the mixing portion 3, being disposed on another end 3b of the mixing portion 3; first blowing ports 6 that introduce the air for combustion to the mixing portion 3 to form a swirling flow with the fuel, being disposed to open to the inner wall of the mixing portion 3; and second blowing ports 7 that additionally introduce the air for combustion to the mixing portion 3, opening in a direction different from the first blowing ports 6 and being disposed further to the other end 3b side of the mixing portion 3 than the swirling flow.

Abstract: A stable continuous production of a propylene-based block copolymer can proceed for a long time without causing accumulation of particles having a small diameter by a process having the following steps: (1) polymerizing an &agr;-olefin containing liquid propylene as a main component in the presence of hydrogen and a stereoregular polymerization catalyst in one or more polymerization reactors to obtain a polymer slurry; (2) feeding the polymer slurry to a copolymerization reactor; and (3) copolymerizing propylene and an &agr;-olefin other than propylene substantially in a gaseous phase in the presence of the stereoregular polymerization catalyst, the polymer slurry and a deactivating compound in the copolymerization reactor to obtain a propylene-block copolymer powder.