Download Applications of Turbulent and Multiphase Combustion by Kenneth K. Kuo, Ragini Acharya(auth.) PDF

By Kenneth K. Kuo, Ragini Acharya(auth.)

A hands-on, built-in method of fixing combustion difficulties in varied parts

An knowing of turbulence, combustion, and multiphase reacting flows is vital for engineers and scientists in lots of industries, together with energy genera-tion, jet and rocket propulsion, toxins keep an eye on, hearth prevention and defense, and fabric processing. This publication bargains a hugely sensible dialogue of burning habit and chemical methods taking place in assorted fabrics, arming readers with the instruments they should clear up the main advanced combustion difficulties dealing with the medical neighborhood this present day. the second one of a two-volume paintings, purposes of Turbulent and Multiphase Combustion expands on themes related to laminar flames from Professor Kuo's bestselling booklet ideas of Combustion, moment variation, then builds upon the speculation mentioned within the better half quantity basics of Turbulent and Multiphase Combustion to deal with intimately state of the art experimental thoughts and purposes now not coated at any place else.

Special beneficial properties of this ebook contain:

  • Coverage of complex purposes similar to good propellants, burning habit, and chemical boundary layer flows

  • A multiphase platforms method discussing easy recommendations ahead of relocating to higher-level purposes

  • A huge variety of functional examples gleaned from the authors' event besides difficulties and a suggestions manual

Engineers and researchers in chemical and mechanical engineering and fabrics technology will locate functions of Turbulent and Multiphase Combustion an vital consultant for upgrading their abilities and maintaining with this swiftly evolving region. it's also a very good source for college kids and execs in mechanical, chemical, and aerospace engineering.Content:
Chapter 1 strong Propellants and their Combustion features (pages 1–71):
Chapter 2 Thermal Decomposition and Combustion of Nitramines (pages 72–142):
Chapter three Burning habit of Homogeneous sturdy Propellants (pages 143–208):
Chapter four Chemically Reacting Boundary?Layer Flows (pages 209–329):
Chapter five Ignition and Combustion of unmarried vigorous sturdy debris (pages 330–455):
Chapter 6 Combustion of reliable debris in Multiphase Flows (pages 456–506):

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Extra resources for Applications of Turbulent and Multiphase Combustion

Sample text

The thermal decomposition of ADN was studied by Brill et al. (1993) by using T-jump/FTIR spectroscopy with fast heating (2,000 K/s) of thin films on a platinum ribbon to a specified constant temperature between 220◦ and 300◦ C. Brill et al. R4) At the onset of decomposition, gas evolution and sharp exothermicity occurred. The initial species observed were NH3 , HNO3 , and N2 O in comparable amounts and a small amount of NO2 and ammonium nitrate (AN, chemical formula: NH4 NO3 ). R6) BACKGROUND OF SOLID PROPELLANT COMBUSTION 37 Brill et al.

A review of these methods has been given in a paper by Zarko and Kuo (1994). In general, there are two major categories for burning rate measurements: (1) standard strand burners method (also called Crawford burners), and (2) small-scale ballistic evaluation motors with known propellant web thickness. These two methods are described in the next subsections. In the second method, the motor firing is conducted and pressure-time traces are measured; along with the web thickness of the propellant, they are used to deduce the burning rate of the propellant.

On such a plot, the subsurface temperature profile should show a linear relationship in the solid-phase region, and the gas-phase temperature profile should show a departure from this straight line. Therefore, the location of the burning surface and the surface temperature can be determined from the departure point from the straight-line section. 8) BACKGROUND OF SOLID PROPELLANT COMBUSTION 21 If Where, Tf Cc: Condense phase Flame temperature specific heat [d g k rb: Propellant burning rate T: Temperature − Ts Surface temperature x] 0 Qs: Heat of reaction at /d T [d the surface per mass p k k : Prop.

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