Mitsubishi Heavy Industries Limited

Other

Tohoku Electric Power Company, Inc.

Mitsuru Inada

Shigemi Mandai

Satoshi Tanimura

Koichi Nishida

Kouichi Akagi

Shinji Akamatsu

Tatsuo Ishiguro

Hideki Haruta

Masataka Ohta

Masataka Ota

Koji Watanabe

Katsunori Tanaka

Minoru Sato

Kensuke Futahashi

Kuniaki Aoyama

Kotaro Miyauchi

Atsushi Moriwaki

Masaaki Nagase

Yoshichika Sato

Jun Kubota

Shozo Hidaka

Shuhei Hosaka

Kouichi Nishida

Kohei Kojima

Yuichi Kobayashi

Kiryo Igarashi

Akio Ogose

A thrust control valve equipped with: a valve element, in which a gas injection passage, through which an operating gas is injected, is formed, with a valve-seating surface being formed in the gas injection passage; and a valve stem, which is provided in the interior of the gas injection passage and has a seated surface that makes contact with the valve-seating surface. A guide surface which makes contact with the inner circumferential surface of the gas injection passage of the valve element is formed on the outer circumferential surface of the valve stem. The guide surface is formed downstream from the seated surface in the direction of flow of the operating gas. A V-groove through which the operating gas flows is formed at the tip of the valve stem, downstream from the seated surface in which the guide surface is formed.

Thrust control valve and flying object

A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.

Pilot nozzle of gas turbine combustor

A pre-mixture forming swirler in a gas turbine pre-mixed flame type low NO combustor is improved so as to accelerate mixing of fuel and air and to prevent the occurrence of flame stagnation and burning of components. In particular, a three-dimensional swirler is constructed such that each swirler vane is twisted from a hub side thereof to a tip side so that a fitting angle of the tip side relative to a center axis of a fuel nozzle is larger than an angle of the hub side. Thereby, while the angle of the hub side is set smaller so that flame stagnation and burning of components resulted therefrom may be prevented from occurring, the angle of the tip side may be selected so that the shearing flow necessary for appropriate mixing of fuel and air is obtained. Thus, favorable pre-mixing is achieved, life deterioration due to burning, etc., is prevented and combustion efficiency is enhanced.

Three-dimensional swirler in a gas turbine combustor

Gas turbine combustor tail tube cooling structure is improved so that temperature distribution along tail tube axial direction is made gentle and large thermal stress is prevented from occurring resulting in enhancement of safety and reliability of the combustor tail tube. Supply jacket (,) is disposed between upstream side discharge jacket (,) and downstream side discharge jacket (,). The upstream side discharge jacket (,) is disposed apart from tail tube inlet (,) at position close to by-pass passage (,) so as to form non-cooled zone (A) in the vicinity of the tail tube inlet (,). On the downstream side thereof, the supply jacket (,) is disposed at position in tail tube (,) contracting portion and near the downstream side discharge jacket (,) so as to shorten length of cooling pipes there.

Cooling structure for combustor tail pipes

Gas turbine combustor

This invention concerns the use of pressurized steam as the cooling medium for a gas turbine combustor. It is distinguished by the following. Steam supply manifolds or ports for the cooling steam are provided on the gas inlet and outlet sides of the combustion chamber in the gas turbine combustor. A steam exhaust manifold or port for the cooling steam is provided between the gas inlet and outlet sides, in approximately the center of the chamber. Cooling channels for the steam are created in the external wall panel of the chamber between the steam supply manifolds and the exhaust manifold. The steam supplied into the wall panel through the steam supply manifolds on the gas inlet and outlet sides of the chamber is exhausted to the exterior via the steam exhaust manifold in the center of the chamber. This design allows pressurized steam with a high thermal capacity to be used to effectively cool the wall panels of the combustor, which are exposed to extremely hot combustion gases.

Steam cooling method for gas turbine combustor and apparatus therefor

Steam cooling type gas turbine combustor

A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.

Combustor

A multi-nozzle combustor comprising a pilot nozzle for flame retention and a plurality of main nozzles arranged around the pilot nozzle, each of the nozzles including an outer cylinder, an inner cylinder, and an annular passage defined between the outer and inner cylinders and forming therein a mixture-evaporation region for a fuel ejected and atomized by an airflow.

Multi-nozzle combustor

Growing community of inventors

Hyogo, Japan

Mitsuru Inada