MITSUBISHI POWER, LTD.

A high-temperature component according to an embodiment is a high-temperature component which requires to be cooled by a cooling medium, and includes: a plurality of cooling passages through which the cooling medium is able to flow; and a first partition wall disposed inside each of the cooling passages to partition the cooling passage into a plurality of first branch flow passages. The first partition wall includes an oblique portion formed such that, in an upstream side region of the first partition wall, a flow-passage cross-sectional area of the cooling passage as seen in an extension direction of the cooling passage gradually decreases from an upstream side toward a downstream side.

A turbine blade includes an airfoil portion, a cooling passage inside the airfoil portion, and a plurality of cooling holes formed in a trailing edge part of the airfoil portion. The cooling holes communicating with the cooling passage and opening in a surface of the trailing edge part. A relation of d_up<d_mid<d_down is satisfied, where d_mid is an index indicating opening densities of the cooling holes in a center region including an intermediate position between a first end and a second end of the airfoil portion in the blade height direction, d_up is an index in a region positioned upstream of a flow of a cooling medium in the cooling passage from the center region in the blade height direction, and d_down is an index in a region positioned downstream of the flow of the cooling medium from the center region in the blade height direction.

A turbine stator blade ( 21 ) includes a pressure side ( 21 P) extending in a radial direction intersecting a flow direction of steam, and facing upstream in the flow direction. A slit ( 5 ) extending in the radial direction and capturing a liquefied component of the steam is formed on a downstream side of the pressure side ( 21 P). A hydrophilic uneven region ( 6 ) having a liquid film capacity greater than that of the pressure side ( 21 P) by being recessed in a depth direction intersecting the pressure side ( 21 P) is formed in a further upstream position than the slit ( 5 ). The hydrophilic uneven region ( 6 ) has a depth in the depth direction increasing and a flow resistance decreasing toward downstream and toward the slit ( 5 ).

A turbine stator blade ( 21 ) includes a pressure side ( 21 P) extending in a radial direction intersecting a flowing direction of steam and facing upstream in the flowing direction. A slit ( 5 ) capturing droplets generated by liquefaction of the steam is formed on a downstream side of the pressure side ( 21 P). A fine uneven region ( 6 ), which guides the droplets attached to the pressure side ( 21 P) in the radial direction such that the droplets are moved toward the slit ( 5 ) and from upstream toward downstream, is formed in a further upstream position than the slit ( 5 ). The fine uneven region ( 6 ) has a flow resistance to the droplets gradually increasing from inward to outward in the radial direction.

The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity. When viewed from the combustion chamber, slits extending radially are formed in the base frame such that each separate the circumferentially adjacent fuel nozzles from each other.

To prevent or reduce an oversensitive change in the degree of opening of a bleed valve regulating the flow volume of a cooling air used to heat a fuel. A gas turbine includes: a compressor compressing an air; a combustor burning a fuel mixed with the air compressed by the compressor; a turbine configured to be driven by a combustion gas generated by the combustor; a heat exchanger causing the fuel to be supplied to the combustor to be heated through a cooling air bled from the compressor to be supplied to the turbine; a bleed valve regulating the flow volume of the cooling air; a first sensor measuring a fuel state value; a second sensor measuring a cooling air state value; and a control computer controlling the degree of opening of the bleed valve. The control computer stores therein data on reference values and dead bands including the corresponding reference value set for each of the fuel state value and the cooling air state value, and, when a measured value of at least one of the fuel state value and the cooling air state value has changed so much away from the corresponding reference value as to fall outside the corresponding dead band, controls the bleed valve such that the changed measured value is brought close to the corresponding reference value.

A resonant sound absorbing device of a gas turbine combustor includes a plurality of resonance chambers independently disposed side by side in an axial direction of the gas turbine combustor so as to communicate with a gas passage of the gas turbine combustor via acoustic holes. The plurality of resonance chambers include n related resonance chambers each satisfying: 0.9 × ∑ i = 1 n ⁢ F i n ≤ F i ≤ 1.1 × ∑ i = 1 n ⁢ F i n ( A ) where n is an integer of 2 or more, and Fi is a peak frequency corresponding to a maximum sound absorbing ratio of the ith related resonance chamber of the n related resonance chambers.

This cooling equipment comprises: a refrigerant supply line ( 81 ) supplying, to a condenser ( 6 ), a condenser refrigerant which cools steam (Sb) that has driven a steam turbine ( 5 ), to return the steam (Sb) to water (W); and a cooling part ( 80 ) which is disposed on the refrigerant supply line ( 81 ), and performs heat exchange between liquefied gas used as fuel for a gas turbine ( 2 ) and the condenser refrigerant to heat and vaporize the liquefied gas and to cool the condenser refrigerant at the same time.

A first-stage stator vane for a gas turbine includes: a first portion partially defining an airfoil which includes a pressure surface, a suction surface, and a trailing edge; and a second portion positioned at a leading-edge side of the airfoil with respect to the first portion, the second portion having a recess portion or a protruding portion. The recess portion or the protruding portion has a pair of side wall surfaces, and an angle formed between the pair of side wall surfaces is less than 90 angular degrees.

The gas turbine nozzle has nozzles formed integrally through an inner endwall and an outer endwall. The inner endwall has an upstream connection portion, a downstream connection portion, and an inner endwall body. The upstream connection portion extends radially inward and is connected to the inner turbine diaphragm. The downstream connection portion is located downstream from the upstream connection portion, extends radially inward, and is connected to the inner turbine diaphragm. The inner endwall body extends from upstream toward downstream and the upstream connection portion and the downstream connection portion are formed on the inner endwall body. The inner endwall body has a digging area that is dug radially outward in a position between the upstream connection portion and the downstream connection portion, and an impingement cooling plate is installed on a surface of the digging area.