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  • 1
    Publication Date: 2006-10-26
    Description: Hydrogen convective cooling of rocket nozzles
    Keywords: PROPELLANTS
    Format: text
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  • 2
    Publication Date: 2006-04-20
    Description: Characteristics of fans and compressors for aircraft turbine engines
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 1-36
    Format: text
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  • 3
    Publication Date: 2006-10-26
    Description: High pressure-ratio multistage axial flow compressor operation efficiency with one or more blade rows stalled - performance prediction
    Keywords: AERODYNAMICS
    Format: text
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  • 4
    Publication Date: 2019-06-27
    Description: A two-stage axial-flow fan with a tip speed of 1450 ft/sec (442 m/sec) and an overall pressure ratio of 2.8 was designed, built, and tested. At design speed and pressure ratio, the measured flow matched the design value of 184.2 lbm/sec (83.55kg/sec). The adiabatic efficiency at the design operating point was 85.7 percent. The stall margin at design speed was 10 percent. A first-bending-mode flutter of the second-stage rotor blades was encountered near stall at speeds between 77 and 93 percent of design, and also at high pressure ratios at speeds above 105 percent of design. A 5 deg closed reset of the first-stage stator eliminated second-stage flutter for all but a narrow speed range near 90 percent of design.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3076 , E-7851
    Format: application/pdf
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  • 5
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    In:  CASI
    Publication Date: 2016-06-07
    Description: The highlights of the NASA program on transonic compressors are presented. Effects of blade shape and throat area on losses and flow range are discussed. Some effects of casing treatment on stall margin are presented. Results of tests with varying solidity are also presented. High Mach number, highly loaded stators are discussed and some results of stator hub slit suction are presented.
    Keywords: MECHANICAL ENGINEERING
    Type: Pennsylvania State Univ. Fluid Mech., Acoustics, and Design of Turbomachinery, Pt. 2; p 581-602
    Format: application/pdf
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  • 6
    Publication Date: 2019-07-13
    Description: NASA has funded two separate contracts to apply pulsed laser holographic interferometry to the detection of shock patterns in the outer span regions of high tip speed transonic rotors. The first holographic approach used ruby laser light reflected from a portion of the centerbody just ahead of the rotor. These holograms showed the bow wave patterns upstream of the rotor and the shock patterns just inside the blade row near the tip. The second holographic approach, on a different rotor, used light transmitted diagonally across the inlet annulus past the centerbody. This approach gave a more extensive view of the region bounded by the blade leading and trailing edges, by the part span shroud and by the blade tip. These holograms showed the passage shock emanating from the blade leading edge and a moderately strong conical shock originating at the intersection of the part span shroud leading edge and the blade suction surface.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ASME PAPER 74-GT-46 , Gas Turbine Conference and Products Show; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
    Format: text
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  • 7
    Publication Date: 2019-07-13
    Description: Pulsed laser holographic interferometry has been applied to the detection of shock patterns in the outer span regions of high tip speed transonic rotors. The first holographic approach used ruby laser light reflected from a portion of the centerbody just ahead of the rotor. These holograms showed the bow wave patterns upstream of the rotor and the shock patterns just inside the blade row near the tip. Much of the region of interest was in the shadow of the blade leading edge and could not be visualized. The second holographic approach, on a different rotor, used light transmitted diagonally across the inlet annulus past the centerbody. This approach gave a more extensive view of the region bounded by the blade leading and trailing edges, by the part span shroud and by the blade tip. These holograms showed the passage shock emanating from the blade leading edge and a moderately strong conical shock originating at the intersection of the part span shroud leading edge and the blade suction surface. Reasonable details of the shock patterns were obtained from holograms which were made without extensive rig modifications.
    Keywords: MASERS
    Type: NASA-TM-X-71430 , E-7622 , Intern. Gas Turbine Conf; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
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  • 8
    Publication Date: 2019-06-27
    Keywords: unknown
    Type: NACA-RM-SE57G17
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-27
    Description: Rapid double-pulsed holographic techniques were used to visualize the shock configurations in the tip region of a lightly loaded, high tip speed fan stage. The holograms showed the passage shock emanating from the blade leading edge, a moderately strong conical shock originating at the intersection of the part span shroud leading edge and the blade suction surface, and a second conical shock originating at the intersection of the part span shroud and the blade pressure surface. Due to a limited viewing angle, the bow waves upstream of the rotor could not be observed, and only limited details of the trailing edge shocks were obtained. Reasonable details of the shock patterns were obtained from holograms which were made without extensive rig modifications. Results indicate that larger viewing windows and and holographic plates would permit a wider viewing angle and give much more coverage of the regions of interest. Also, shorter time delay for double-pulsed holograms is also desirable, and would minimize blade movement and give clearer holograms.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-X-71788 , E-7622
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  • 10
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Eng. Stall and Surge; 19 p
    Format: text
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