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    • 8. 发明专利
    • GAS TURBINE
    • JP2001349202A
    • 2001-12-21
    • JP2000174209
    • 2000-06-06
    • HITACHI LTD
    • KITSUKA NOBUAKIKAWAIKE KAZUHIKOANZAI SHUNICHIUENO SANEYUKI
    • F01D9/02F01D11/04
    • PROBLEM TO BE SOLVED: To provide a gas turbine capable of simplifying the constitution of a separating part of a closed cooling medium passage and an open cooling medium passage and capable of sufficiently preventing a leak of a refrigerant and supercooling of a blade part. SOLUTION: In this gas turbine having cooling medium flowing paths inside a turbine stationary blade 3 and formed so as to cool the stationary blade by making a cooling medium to flow to these cooling medium flowing paths, to partially recover the cooling medium after cooling the stationary blade and to blow off a part in main flow gas 20, the plural cooling medium flowing paths are arranged in the stationary blade 3, and at least one cooling medium flowing path in these cooling medium flowing paths cools the stationary blade by flow of the cooling medium supplied from an external part, and the cooling medium is recovered again after cooling, and the other cooling medium flowing path is formed so as to cool the stationary blade 3 by flow of the cooling medium 23 supplied from the external part, to blow off the partial cooling medium in the main flow gas 20 after cooling and to supply a cooling medium 23b of a residual part as a sealing medium to a rotary part arranged on the inner peripheral side of the stationary blade.
    • 9. 发明专利
    • GAS TURBINE
    • JP2000045705A
    • 2000-02-15
    • JP21682498
    • 1998-07-31
    • HITACHI LTD
    • MARUSHIMA SHINYAMATSUMOTO MANABUIKEGUCHI TAKASHIKAWAIKE KAZUHIKO
    • F01D5/18F01D5/30
    • PROBLEM TO BE SOLVED: To prevent the lowering of efficiency of a gas turbine while reducing the leaked variable of the coolant by providing seals for restricting the flow-out of the coolant through a clearance between both dovetails between a disc dovetail part of a rotor blade and a blade dovetail part outside of a supplying circuit and a recovering circuit. SOLUTION: During the operation of a gas turbine, the main flow gas is flowed from a first stage rotor blade to a fourth stage rotor blade, and the cooling air is supplied to a center hole of a stub shaft, and supplied to the rotor blade through a radial hole 29 provided in the peripheral side of a disc 1. The air passed through the radial hole 29 is flowed through a rotor blade supply port 122, a rotor blade recovery port 124 and a radial hole 30 so as to cool the rotor blade. In the rotor blade, a clearance 117 exists between a dovetail part 102 and the disc 1 for installation of the dovetail part 102, but seal pins 124-126 are fitted in corresponding opening parts 127-129 so as to prevent the generation of leak of the cooling air along the clearance 117 in the axial direction.
    • 10. 发明专利
    • REFRIGERANT RECOVERY TYPE GAS TURBINE
    • JPH11153001A
    • 1999-06-08
    • JP31929097
    • 1997-11-20
    • HITACHI LTD
    • MATSUMOTO MANABUMARUSHIMA SHINYAIKEGUCHI TAKASHIKAWAIKE KAZUHIKO
    • F01D5/08F02C7/18
    • PROBLEM TO BE SOLVED: To satisfactorily reduce thermal stress of a rotor part that is caused by the recovery of refrigerant for a moving blade and recover the refrigerant efficiently. SOLUTION: This gas turbine comprises a refrigerant supply channel which supplies refrigerant for cooling a moving blade, and a refrigerant recovery channel 71 which recovers the refrigerant which had cooled the moving blade, in its turbine rotor, and is formed to recover the refrigerant which had cooled the moving blade. Heat shield headers 75a and 75b are provided between one of the refrigerant supply channel or the refrigerant recovery channel 71 and the moving blade 40, the heat shield headers 75a and 75b are connected with one of the refrigerant supply channel or the refrigerant recovery channel through at least one connecting passage, and connecting pipes as many as the moving blades 40 are provided between the heat shield header 75 and the moving blade 40, resulting in the supply or the recovery of refrigerant to or from each moving blade 40 through the heat shield headers 75a and 75b and the connecting pipe.