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    • 21. 发明专利
    • FIBER TYPE LASER DOPPLER FLOW METER
    • JPH06308140A
    • 1994-11-04
    • JP9314793
    • 1993-04-20
    • HITACHI LTD
    • KOBAYASHI SHIGEYOSHIINOUE HIROSHIHAYASHI NORIYUKIAZUHATA SHIGERU
    • F23N5/08G01P5/00
    • PURPOSE:To measure flow rate in two-dimensional area by providing a mirror that reflects radiation light to a measurement point so that Doppler signal there is reflected to a photo- detection part and also a radiation part and a fixed part, mutually lacked in such a way they are allowed to move forward and backward in the direction of optical axis of the radiation light to the mirror. CONSTITUTION:The laser light from a laser oscillation device comes, through an optical fiber 4, into a laser radiation/Doppler signal photo-detection part 14, and then radiated by a lens 21, and further reflected on an aluminum-deposited surface 12 of a mirror 11, and then, through a window 17, a crossing paint 24 of the laser light 22 is formed at a speed measurement position in the fluid whose speed is to be measured. When a seed material that flows in the fluid together passes by a crossing point 24, the reflected light containing the Doppler signal issued when detecting the laser light 22 comes, through the window 17, into the mirror 11, and then is reflected and condensed on the photo-detection part 14. The light is introduced into a photomultiplier, and, through photoelectric conversion, comes into a signal process device, so that flow rate at the crossing point 24 is calculated. Alternately, by moving an outside tube 10 in the direction of axis and an inside tube 15 in the direction of axis accordingly, for the position of crossing point 24 to be changed in two-dimensional manner, flow rate may be measured.
    • 27. 发明专利
    • PREMIX-TYPE GAS TURBINE COMBUSTOR
    • JPH04126921A
    • 1992-04-27
    • JP24752090
    • 1990-09-19
    • HITACHI LTD
    • YOKOTA OSAMUISHIBASHI YOJIAKATSU YASUAKIOMORI TAKASHIINOUE HIROSHI
    • F23R3/12F23R3/28F23R3/30
    • PURPOSE:To make uniform the flow velocity of a premix and the distribution of fuel concentration at a swirler outlet in a premix combustion part, by forming swirler vanes disposed in a swirler of the premix combustion part in the shape of fins, in a multi-nozzle type two-stage combustor. CONSTITUTION:In diffusion combustion 1 in a multi-nozzle type two-stage combustor, a primary fuel ejected from a primary fuel nozzle 3 and primary air 4 are mixed with each other by diffusion, and a flame is formed in a region where the fuel concentration is within a combustible concentration range from a low to a high concentration. In a premix combustion 2, a secondary fuel ejected from a secondary fuel nozzle 5 and secondary air 6 are premixed with each other in a swirler 7, to form a flame at an outlet of the swirler 7. Fin- shaped swirler vanes 8 provided in the swirler 7 in a premix combustion part cause the secondary fuel and the secondary air 6 flowing on the fins to generate swirls at upstream and downstream ends of the fins, thereby accelerating the mixing. It is thereby possible to make uniform the flow velocity of the premix and the distribution of fuel concentration at the swirler outlet, within a short distance and without causing any pressure loss in the premix blowing through the swirler.
    • 28. 发明专利
    • FLAME HOLDER
    • JPH0490403A
    • 1992-03-24
    • JP20501390
    • 1990-08-03
    • HITACHI LTD
    • INOUE HIROSHIYOKOTA OSAMUKOBAYASHI SHIGEYOSHI
    • F23D11/24
    • PURPOSE:To obtain a compact gas turbine combustion apparatus so as to induce a vortex flow having an axis in the direction of a main flow by changing the position of the direction of a suddenly expanding main flow continuously or by stages in the direction parallel with a wall surface while being crossed at a right angle with the main flow. CONSTITUTION:Main fuel F is injected into a premixing chamber 9 from a main fuel nozzle 8 mounted on a concentric circle to a pilot burner and changed into an unburnt pre-mixture, and flows into a combustion chamber 11. The pre-mixture forms a pre-mixed flame 6, the central side of which is ignited and stabilized by a pilot burner and the outer circumferential side of which by the circulating flow of a suddenly expanding section 1, at that time. Since the suddenly expanding section 1 is formed in a notched-shaped recessed section 2, the sectional shape of the pre-mixed flame 6 is formed in a planar shape, and the pre-mixed flame is shortened, and combustion is completed in front of a diluted air hole 12. Accordingly, a gas turbine combustion apparatus can be miniaturized.