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  • 1
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    Turbofan compressor dynamics during afterburner transients (1976)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The effects of afterburner light-off and shut-down transients on the compressor stability are investigated. The reported experimental results are based on detailed high response pressure and temperature measurements on the TF30-P-3 turbofan engine. The tests were performed in an altitude test chamber simulating high altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shutdown transient the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Unsteady Phenomena in Turbomachinery; 12 p
    Format: text
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  • 2
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    Formulation of blade-flutter spectral analyses in stationary reference frame (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Analytic representations are developed for the discrete blade deflection and the continuous tip static pressure fields in a stationary reference frame. Considered are the sampling rates equal to the rotational frequency, equal to blade passing frequency, and for the pressure, equal to a multiple of the blade passing frequency. For the last two rates the expressions for determining the nodal diameters from the spectra are included. A procedure is presented for transforming the complete unsteady pressure field into a rotating frame of reference. The determination of the true flutter frequency by using two sensors is described. To illustrate their use, the developed procedures are used to interpret selected experimental results.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-2296 , E-1888 , NAS 1.60:2296
    Format: application/pdf
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  • 3
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    Measurements of self-excited rotor-blade vibrations using optical displacements (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The characteristics of optical displacement spectra and their role of monitoring rotor blade vibrations are discussed. During the operation of a turbofan engine at part speed, near stall, and elevated inlet pressure and temperature, several vibratory instabilities were excited simultaneously on the first fan rotor. The torsional and bending contributions to the main flutter mode were resolved by using casing-mounted optical displacement sensors. Other instabilities in the blade deflection spectra were identified. Previously announced in STAR as N83-14523
    Keywords: STRUCTURAL MECHANICS
    Type: ASME PAPER 83-GT-132 , ASME, Transactions, Journal of Engineering for Gas Turbines and Power (ISSN 0022-0825); 106; 44-49
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  • 4
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    Mixing of supersonic jets including the effects of supersonic jets including the effects of transverse pressure gradient using difference methods (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The usual boundary-layer equations describing the steady-state mixing of parallel jets are supplemented by the momentum equation in the direction normal to the flow. This allows detailed computation of the flow field in the mixing region and simultaneous computation of the outer inviscid flow. An explicit and an implicit finite difference scheme have been developed and applied in several illustrative examples. The examples include mixing of planar and axisymmetric supersonic jets of different composition with both matched and unmatched static pressures. Numerical results were compared with available experimental data obtained for the unmatched pressure case.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-6592 , E-6386
    Format: application/pdf
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  • 5
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    Supersonic combustion of hydrogen in a vitiated air stream using stepped wall injection (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Combustion physics and ignition of hydrogen in supersonic stream of vitiated air or inert gases using stepped-wall injection procedure
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-67840
    Format: application/pdf
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  • 6
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    Measurement of Gust Response on a Turbine Cascade (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The paper presents benchmark experimental data on a gust response of an annular turbine cascade. The experiment was particularly designed to provide data for comparison with the results of a typical linearized gust-response analysis. Reduced frequency, Mach number, and incidence were varied independently. Except for the lowest reduced frequency, the gust velocity distribution was nearly sinusoidal. For the high inlet-velocity series of tests, the cascade was near choking. The mean flow was documented by measuring blade surface pressures and the cascade exit flow. High-response pressure transducers were used to measure the unsteady pressure distribution. Inlet-velocity components and turbulence parameters were measured using hot wire. In addition to the synchronous time-average pressure spectra, typical power spectra are included for several representative conditions.
    Keywords: AERODYNAMICS
    Type: NASA-TM-106776 , E-9227 , NAS 1.15:106776 , Turbo Expo 1995; Jun 05, 1995 - Jun 08, 1995; Houston, TX; United States
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  • 7
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    Measurement of aerodynamic work during fan flutter (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: (Previously announced in STAR as N81-25080)
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Fluid/structure interactions in turbomachinery; Nov 15, 1981 - Nov 20, 1981; Washington, DC
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  • 8
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    Diffusive ignition and combustion in a wall jet (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hydrogen is injected from a downstream facing step in a wall into a high-temperature stream. Temperature and hydroxyl radical concentration are measured downstream of the injection plane by means of ultraviolet absorption spectroscopy. The experimental results are compared with theory which is based on a finite-difference solution of boundary-layer equations. Finite-rate kinetics equations are included in the analysis. The analytic predictions are also compared with previously obtained experimental results which are based on probe measurements. Comparison is made between calculated and observed ignition distances.
    Keywords: PROPULSION SYSTEMS
    Type: Joint Fluids Engineering Conference; May 13, 1974 - May 15, 1974; Montreal; Canada
    Format: text
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  • 9
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    Turbofan compressor dynamics during afterburner transients (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effects of afterburner light-off and shut-down transients on compressor stability were investigated. Experimental results are based on detailed high-response pressure and temperature measurements on the Tf30-p-3 turbofan engine. The tests were performed in an altitude test chamber simulating high-altitude engine operation. It is shown that during both types of transients, flow breaks down in the forward part of the fan-bypass duct. At a sufficiently low engine inlet pressure this resulted in a compressor stall. Complete flow breakdown within the compressor was preceded by a rotating stall. At some locations in the compressor, rotating stall cells initially extended only through part of the blade span. For the shutdown transient, the time between first and last detected occurrence of rotating stall is related to the flow Reynolds number. An attempt was made to deduce the number and speed of propagation of rotating stall cells.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71741 , E-8375 , Symp. on Unsteady Phenomena in Turbomachinery; Sep 22, 1975 - Sep 26, 1975; Monterey, CA; United States
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  • 10
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    Diffusive ignition and combustion in a wall jet (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hydrogen is injected from a downstream facing step in a wall into a high-temperature stream. Temperature and hydroxyl radical concentration are measured downstream of the injection plane by means of ultraviolet absorption spectroscopy. The experimental results are compared with theory which is based on a finite-difference solution of boundary-layer equations. Finite-rate kinetics equations are included in the analysis. The analytic predictions are also compared with previously obtained experimental results which are based on probe measurements. Comparison is made between calculated and observed ignition distances.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-71496 , E-7810 , Symp. on the Fluid Mech. of Combust.; May 13, 1974 - May 16, 1974; Montreal
    Format: application/pdf
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