Ihi Corporation

Ishikawajima-harima Heavy Industries Co., Ltd.

Jun Hosoi

Shinji Tanaka

Katsuyoshi Takahashi

Nagayoshi Hiromitsu

Junichi Sato

Atsushi Fujii

Yoji Okita

Chiyuki Nakamata

Yuuta Matsumoto

Tsukasa Saitou

Dirk Riechelmann

Tomoaki Yoshida

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.

Engine aft section structure

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.

Thrust increasing device

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 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.

Afterburner and aircraft engine

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.

A burnerfor combustion chamber is provided with a cylindrical mixing portionthat mixes air for combustion (oxidizing agent) and fuel in the interior thereof and has one endthat opens to a combustion portion; a spray nozzle (fuel spraying portion)that sprays fuel in the mixing portion, being disposed on another endof the mixing portion; first blowing portsthat introduce the air for combustion to the mixing portionto form a swirling flow with the fuel, being disposed to open to the inner wall of the mixing portion; and second blowing portsthat additionally introduce the air for combustion to the mixing portion, opening in a direction different from the first blowing portsand being disposed further to the other endside of the mixing portionthan the swirling flow. The burner for combustion chamber and combustion method of the present invention can shorten the flame length in the central axial direction by improving the combustion efficiency even during low loading and shorten the overall length of the burner for combustion chamber in the central axial direction.

Growing community of inventors

Tokyo, Japan

Jun Hosoi