The Experts below are selected from a list of 15 Experts worldwide ranked by ideXlab platform

S Greenfield - One of the best experts on this subject based on the ideXlab platform.

  • dilution of cryogenic Liquid Rocket Propellants during pressurized transfer
    Aircraft Engineering and Aerospace Technology, 2013
    Co-Authors: S Greenfield
    Abstract:

    In the testing of Rocket engines and engine components, such as thrust chambers and gas generators, the Rocket engineer is regularly faced with the job of transferring cryogenic Liquid Propellants, using pressure feed from a storage tank, through a flow system and into the combustion device to be tested. At Rocketdyne, Liquid oxygen is quite commonly used as a propellant. In the testing of engine components inert pressurants are usually used, for example, helium or nitrogen. However, because of the cost and logistics, nitrogen is preferred. When gaseous nitrogen is used as the pressurant, we have repeatedly run into testing conditions which have resulted in condensation of nitrogen and subsequent mixing in the tanked Liquid oxygen. This dilution of the Liquid oxygen effects a loss of performance and imposes mechanical difficulty in maintaining a regulated propellant tank pressure.

Zheng Hongjian - One of the best experts on this subject based on the ideXlab platform.

  • storing technique of Liquid Rocket Propellants
    Aerospace Shanghai, 2001
    Co-Authors: Zheng Hongjian
    Abstract:

    Considering corrosiveness, volatility, hygroscopicity and poisonousness of liqui d Rocket Propellants, The method of storing Propellants and matters needing atte ntion are presented in this paper. Technical measures are provided for storing p ropellants safely and effectively for the army with certain economic and militar y profit as well as social benefit.

W. E. Moeckel - One of the best experts on this subject based on the ideXlab platform.

  • NATIONAIIADVISORY CCWITTTE FOR AERONAUTICS
    2016
    Co-Authors: Surface Coolants, W. E. Moeckel
    Abstract:

    Analysis is made of the propulsive thrust and spectiic impulse attainable by coolhg aticraft surfaces with liquefied or solidified gases havbg vaporization temperatures lower tlum the equilibrium sur-face temperature. lt is found that for some coolants a net thrust is obtainable without further heat additim at all flight speeds if the vaporizatim temperature and heat of vaporization are suffici~t ly low. Use of coolant vaporization as the sole means of propulsion yields low specific Impulses at low speeds. As flight speed fncreases, the attainable specific impulse increases; if Liquid hydrogen is used as coolant, specifio Impulses cmnpaz’ableto those of conventional Liquid Rocket Propellants are theoretically attainable in the hyperstiic speed range. This propulsion system provides the possibility of flight with cooled aircraft surfaces at extremely high Mach numbers. As an auxiliary power source

Patrick Vuillermoz - One of the best experts on this subject based on the ideXlab platform.

  • european research and technology test bench p8 for high pressure Liquid Rocket Propellants
    36th AIAA ASME SAE ASEE Joint Propulsion Conference and Exhibit, 2000
    Co-Authors: Andreas Haberzettl, Dieter Gundel, Klaus Bahlmann, Jean Thomas, Joachim Kretschmer, Patrick Vuillermoz
    Abstract:

    In 1995 the partners CNES, Dasa, SEP and DLr started the operation of the European research and technology test bench P8. This test facility designed for high pressure GH2/LOX combustion is jointly used by the partners in order to concentrate research and technology activities. The main objective is to increase the basic knowledge about the governing processes inside the combustion chamber at high pressures and to advance new combustor technologies for future cryogenic engines. Since 1995 a large number of successful experiments and test campaigns have been carried out concerning new technological developments as thermal barrier coatings, ceramic cooling elements, supersonic nozzles, injection elements and subscale models of upper stage combustion chambers. In the field of combustion research new results about the behaviour of the atomisation and reactive flow phenomena have been gained. Designing future engines requires a reliable analysis of the thermal boundary conditions. Especially the expander cycle requires good heat transfer behaviour of the chamber walls in order to heat up the cryogenic hydrogen efficiently.

Andreas Haberzettl - One of the best experts on this subject based on the ideXlab platform.

  • european research and technology test bench p8 for high pressure Liquid Rocket Propellants
    36th AIAA ASME SAE ASEE Joint Propulsion Conference and Exhibit, 2000
    Co-Authors: Andreas Haberzettl, Dieter Gundel, Klaus Bahlmann, Jean Thomas, Joachim Kretschmer, Patrick Vuillermoz
    Abstract:

    In 1995 the partners CNES, Dasa, SEP and DLr started the operation of the European research and technology test bench P8. This test facility designed for high pressure GH2/LOX combustion is jointly used by the partners in order to concentrate research and technology activities. The main objective is to increase the basic knowledge about the governing processes inside the combustion chamber at high pressures and to advance new combustor technologies for future cryogenic engines. Since 1995 a large number of successful experiments and test campaigns have been carried out concerning new technological developments as thermal barrier coatings, ceramic cooling elements, supersonic nozzles, injection elements and subscale models of upper stage combustion chambers. In the field of combustion research new results about the behaviour of the atomisation and reactive flow phenomena have been gained. Designing future engines requires a reliable analysis of the thermal boundary conditions. Especially the expander cycle requires good heat transfer behaviour of the chamber walls in order to heat up the cryogenic hydrogen efficiently.