Abstract: 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.

Abstract: 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.

Abstract: A fluid composition analysis mechanism includes a light source for configured to irradiate excitation light to a sample fluid at a measurement position; a light receiving unit arranged on an extended line of the excitation light for configured to receive and disperse Raman scattering light generated from the sample fluid irradiated with the excitation light; a Raman scattering light collection optical system arranged on an optical path for the excitation light or on the extended line of the excitation light configured to collect the Raman scattering light generated at the measurement position and to cause the condensed Raman scattering light to be incident on the light receiving unit; a calculation unit configured to calculate a composition of the sample fluid based on an output of the light receiving unit; and a light shielding member arranged on the optical path or on the extended line of the excitation light.

Abstract: A fluid composition analysis mechanism includes a light source for applying excitation light to a sample fluid at a measurement position, a light receiving unit configured to receive and disperse Raman scattering light generated from the sample fluid irradiated with the excitation light, a Raman scattering light collection optical system configured to collect the Raman scattering light generated at the measurement position and to cause the Raman scattering light to be incident on the light receiving unit, a calculation unit for calculating a composition of the sample fluid based on an output of the light receiving unit, and a light shielding member arranged on the optical path of the excitation light or on the extended line of the excitation light.

Abstract: 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.

Abstract: 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.

Abstract: A pre-mixture forming swirler in a gas turbine pre-mixed flame type low NOx 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.

Abstract: A pre-mixture forming swirler in a gas turbine pre-mixed flame type low NOx 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 (101a) is twisted from a hub side thereof to a tip side so that a fitting angle (&bgr;) of the tip side relative to the center axis (C) of the fuel nozzle (102) is larger than the angle (&agr;) of the hub side. Thereby, while the angle (&agr;) of the hub side is set smaller so that flame stagnation and burning of components resulted therefrom may be prevented from occurring, the angle (&bgr;) of the tip side may be selected so that the shearing flow necessary for appropriate mixing of fuel (F) and air (A) is obtained. Thus, favorable pre-mixing is achieved, life deterioration due to the burning etc. is prevented and combustion efficiency is enhanced.

Abstract: 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 (16) is disposed between upstream side discharge jacket (14) and downstream side discharge jacket (15). The upstream side discharge jacket (14) is disposed apart from tail tube inlet (2) at position close to by-pass passage (10) so as to form non-cooled zone (A) in the vicinity of the tail tube inlet (2). On the downstream side thereof, the supply jacket (16) is disposed at position in tail tube (1) contracting portion and near the downstream side discharge jacket (15) so as to shorten length of cooling pipes there.

Abstract: To prepare a more homogeneous premixture than that of the device of the prior art thereby to suppress an NOx emission and to lower a fuel feed pressure. A gas turbine combustor comprising: an outer cylinder 106 having main swirlers 101 therein and adapted to be fed with air; and an annular fuel feed manifold 110 disposed at the outer circumference of the outer cylinder 106 on the upstream or downstream side of the main swirlers 101 and having a plurality of nozzle ports 111 communicating with the inside of the outer cylinder 106, so that a fuel is injected from the outer circumference to the center of the air flowing in the outer cylinder 106.

Abstract: 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.

Abstract: This invention concerns the use of pressurized steam as the cooling medium in the combustor wall of a gas turbine combustor. It is distinguished by the following. The combustor wall is configured by 1) a plurality of cooling channels for cooling steam, sealed by an exterior wall panel and a heat-resistant plate which are assembled by soldering or some other method; 2) a supply manifold for supplying the cooling steam into the cooling channels, which is provided on one end of the cooling channels; and 3) a recovery manifold for recovering the cooling steam from the cooling channels, which is provided on another end of the cooling channels. This arrangement can form strong enough steam-channels that do not allow any leakage of the high pressure steam from the cooling system.

Abstract: 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.

Abstract: 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.