摘要:
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.
摘要:
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.
摘要:
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.
摘要:
A gas turbine blade ring is cooled by steam whose temperature, pressure and flow rate are controlled so that a clearance between a moving blade tip and blade ring is maintained appropriately. Steam from a steam turbine bottoming cycle (10) flows into a blade ring cooling passage (8) of a gas turbine (1) via piping (12) for cooling the blade ring. The steam, having cooled the blade ring, is supplied into a transition piece cooling passage (9) of a combustor (3) for cooling the transition piece, and is then recovered into the steam turbine bottoming cycle (10) via piping (14). While the steam cools the blade ring, the temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach a target value. Thus, the clearance is maintained as small as possible in operation and the gas turbine performance is enhanced.
摘要:
A rotor shaft that is supported by a deep groove ball bearing a radial load and a unidirectional thrust load, and by a cylindrical roller bearing for bearing a radial load. Also, a pretension applying means is provided for applying a pretension to the rotor shaft in the same direction as the thrust load which is borne by the deep groove ball bearing.
摘要:
Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system. Therefore, the difference between the metal temperatures of the turbine casing and the exhaust casing becomes very small and the thermal stress exerted on the exhaust casing due to the temperature difference can be largely reduced.
摘要:
The shaft seal structure is based on a leaf seal that includes springs, disposed between the stator blades and the leaf seal ring, to force the leaf seal ring away from the rotation shaft, and pressure guiding grooves for guiding the fluid pressure, through a boundary of planar plates, to a space between the outer peripheral surface of the leaf seal ring and the inner peripheral surface of the stator blade. Also, a turbine may be provided with the leaf seal so as to reduce gas leakage from the high-pressure-region to the low-pressure-region as well as to control the frictional wear between the planar plates and the rotation shaft.
摘要:
An internal cylinder which has the opening section from which combustion gas is blown out is inserted into the tail cylinder which becomes a flow path of the combustion gas, and is engaged with the tail cylinder, while securing a clearance between the edge of the opening section and the internal wall surface of the tail cylinder. Air compressed with a compressor is jetted from the clearance along the internal wall surface of the tail cylinder, and a film of cooling air is formed on the internal wall surface of the tail cylinder.
摘要:
A shaft seal having a high abrasion resistance is disclosed, by which the leakage of the gas from the high-pressure side to the low-pressure side can be reduced. In the shaft seal, flexible leaves are multi-layered to form a ring shape. The shaft seal is mainly arranged around the rotation shaft of a gas turbine or the like. The relevant turbine comprises a casing, a compressor, a rotation shaft, moving blades attached to the rotation shaft, and stationary blades attached to the casing in a manner such that the stationary blades face the moving blades, wherein the shaft seals are provided between a plurality of stationary blades and the rotation shaft wherein the leaves of each shaft seal contact the rotation shaft. Under the rated operating conditions, the top ends of the leaves slightly separate from the surface of the rotation shaft due to the dynamic pressure generated by the rotation of the rotation shaft. When the turbine is not operated, the top ends of the leaves contact the rotation shaft again due to the elastic restoring force of the leaves.
摘要:
Such a rotating blade body is supplied as can prevent not only local wear and deformation but also inadvertent vibration and can maintain cooling efficiency. A rotating blade body consists of a rotor disc 2 and rotating blades 1 which are assembled so as to extend from the outer circumference of the rotor disc 2 in a radial pattern, wherein blade root portions 10 of the rotating blades 1 are engaged into blade grooves 20 which are formed along a direction of a rotating shaft on an edge of the outer circumference of the rotor disc 2. Circulation spaces 25 for the cooling air are formed along the direction of a rotating shaft between the bottom-end portions 10a of the blade root portions 10 and the bottom portions 20a of the blade grooves 20. Pushing-up members 3 which push up the rotating blades 1 outward in a radial direction are inserted into the circulation spaces 25, maintaining circulation of the cooling air.