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4 edition of Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine found in the catalog.

Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine

Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Airplanes -- Turbine-propeller engines

  • Edition Notes

    StatementL. Danielle DiCicco and Brent C. Nowlin and Lizet Tirres.
    SeriesNASA technical memorandum -- 106594.
    ContributionsNowlin, Brent C., Tirres, Lizet., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17796329M
    OCLC/WorldCa31786648

    Brayton Cycle – Turbine Engine. In , an American engineer, George Bailey Brayton advanced the study of heat engines by patenting a constant pressure internal combustion engine, initially using vaporized gas but later using liquid fuels such as kerosene. This heat engine is known as “Brayton’s Ready Motor”.It means, the original Brayton engine used a piston compressor and piston. Knowing the cooling rate of an item is a useful tool in any science experiment. The process can be time-consuming, but the more accurate data that is taken the more accurate your results will be. Graphing the cooling rate on graph paper also can help you visualize and explain the process.

    Considering temperature lowering at the turbine inlet by 30°C through the intermediate heat exchange, the S-CO 2 indirect cycle achieves efficiency of % at turbine inlet temperature of °C and turbine inlet pressure of 20 MPa. This cycle efficiency value is higher by % than that (%) of a He direct cycle at turbine inlet. Maritime Welding Handbook Welding and Related Processes for Repair and Maintenance Onboard 14th edition 2nd revision Notice: All welding is carried out on the welder’s own risk and account. Welding should be executed by a qualified and experienced.

    When checking the subcool condition the technician will measure the temperature of the liquid line, the pressure at that point and subtract the measured temperature from the saturated temperature at the end of the condenser. With the blend you read the saturated temperature next to the pressure in the liquid (bubble point) column of the chart. (a) 9 μm wide side wall cooling channel near the nozzle throat with turbulator ridges. (b) Nozzle endwall cooling channels with 10 μm dia cylindrical turbulators. cooled. Cooling in these MEMS devices is aided by the high thermal conductivity of silicon and by the sophisticated cooling geometries enabled by the flexibility of micro-machining.


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Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine Download PDF EPUB FB2

Due to the restricted size of micro-gas turbines, the difficulty of cooling their radial turbines and raising their inlet temperature has been an ongoing focus in their research. In this paper, a back-disk impingement cooling technology for radial turbines is proposed.

The study focuses on the influence of the non-uniform circumferential flow field generated by radial turbine volutes on the.

Get this from a library. Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine. [L Danielle DiCicco; Brent C Nowlin; Lizet Tirres; United States.

National Aeronautics and Space Administration.]. Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine. Description of a pressure measurement technique for obtaining surface static pressures of a radial turbine.

Composite matrix cooling scheme for small gas turbine combustors. Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine Conference Paper (PDF Available) June with 13 Reads How we measure 'reads'. Abstract. Instrumentation has been installed on the surface of a cooled radial-inflow turbine.

Thermocouples and miniature integrated sensor pressure transducers were installed to measure steady state coolant temperatures, blade wall temperatures, and coolant pressures.

A numerical study to determine the temperature distribution in the rotor of a radial inflow turbine is presented. Internal cooling passages are modeled in the present formulation in order to carry out solid and coolant temperature computations simultaneously resulting in a. A radial outflow turbine of the Hero type, where the expansion process occurs in the rotor, and only reaction forces apply, appears to offer several advantages over axial or radial inflow turbines.

This was first investigated by Comfort [36] and subsequently by House [37].The basic layout of such a machine, as tried, is shown in Fig. House's test results were disappointing with the best.

The mixed-flow radial-inflow turbine and the radial-inflow turbine have slight differences at the blade inlet as shown in Figure The radial-inflow turbine has a full 90° change from the inlet to the exit as the blades are in a radial position. In the mixed-flow impeller.

Cooling technologies have been widely applied to protect the turbine blades at high inlet temperature, which also makes the aero-thermal coupled phenomenon more remarkable. Simultaneous luminescence pressure and temperature measurements on dyed ceramic models for hypersonic wind tunnels.

Measurement of the coolant channel temperatures and pressures of a cooled radial-inflow turbine. DiCicco, B. Nowlin and; Performance of an active cooled system in a simulated endo atmospheric interceptor environment. Advantages and challenges. Compared to an axial flow turbine, a radial turbine can employ a relatively higher pressure ratio (≈4) per stage with lower flow these machines fall in the lower specific speed and power ranges.

For high temperature applications rotor blade cooling in radial stages is not as easy as in axial turbine stages. Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate. Liu. GT ; VT09A doi: Detailed Film Cooling Measurements on a Cylindrical Leading Edge Model: Effect of Free-Stream Turbulence and Coolant Density Effect of Pressure and Turbine Inlet Temperature on the Efficiency of Pressurized Fluidized Bed.

This two-part paper addresses the design of a U-bend for serpentine internal cooling channels optimized for minimal pressure loss. The total pressure loss for the flow in a U-bend. An experimental program has been designed and conducted to model and measure the effects of film coolant injection on convection heat transfer to turbine blade tips.

The modeling approach follows earlier work that found the leakage flow to be mainly a pressure-driven flow related strongly to the the airfoil pressure loading distribution and.

Car engines run remarkably well using combustion fuels and oil for part lubrication. But friction still occurs between the moving parts, leading to heat buildups. If the climbing temperature is not dampened or dissipated, the engine will overheat and stop working.

As a result, engine coolant. Differential pressure flowmeters (Figure 2) measure changes in pressure to determine flow velocity. They feature a flow-restrictive orifice or laminar flow element that evaluates the pressure drop through the restriction.

The pressure drop between upstream and downstream points is proportional to the rate of flow. (a) Cooling at constant pressure followed by heating at constant volume.

(b) Heating at constant volume followed by cooling at constant pressure. Calculate the heat and work requirements and ΔU and ΔH of the air for each path. The following heat capacities for air may be assumed independent of temperature: C V = and C P = J mol-1 K In these experiments a full-scale model of the aft (downstream) cavity of a typical aircraft gas turbine was employed using a high-molecular-weight gas (Refrigerant) at ambient pressure and temperature conditions to match the dimensionless parameters at engine conditions.

The cavity temperature and selected cavity velocity profiles were. A set of tubes is called the tube bundle and can be made up of several types of tubes: plain, longitudinally finned, etc.

Shell and tube heat exchangers are typically used for high-pressure applications (with pressures greater than 30 bar and temperatures greater than °C).

The RBMK (Russian: реактор большой мощности канальный, РБМК; reaktor bolshoy moshchnosti kanalnyy, "high-power channel-type reactor") is a class of graphite-moderated nuclear power reactor designed and built by the Soviet name refers to its unusual design where, instead of a large steel pressure vessel surrounding the entire core, each fuel assembly.

In the example of turbine cooling applications [6], impinging jet flows may influence on bleed air supply pressure and temperature. In addition to high-pressure compressor air, turbofan engines provide cooler fan air at lower The selection of Nusselt number to measure .- Cooled turbine blade types.

Rgure 4. - Wire mesh stator assembly. TRAILING POROUS SKIN EDGE SLOT (DISCRETE HOLES) TOTAL PRESSURE DROP, % CS Figure 6. - Rotor installed. Ut TURBINE EFF, % COOLANT FLOW, % cs-sr Figure 7.

-Turbine stage efficiencies. Figure 8.A coolant scheme enhances the radial turbine's advantages and potential uses. A cooled radial turbine allows operation at a higher inlet temperature. With the ability to operate in a higher temperature regime, the radial turbine can be used as a primary power source, particularly in small turbine engines.

NASA's cooled radial turbine research.