Critical combustion diameter of condensed substances

1974 ◽  
Vol 10 (5) ◽  
pp. 580-587 ◽  
Author(s):  
B. N. Kondrikov ◽  
B. V. Novozhilov
Keyword(s):  
Combustion Diameter ◽  
Critical Combustion

Critical combustion diameter of tetryl

1979 ◽  
Vol 15 (1) ◽  
pp. 47-51 ◽  
Author(s):  
V. �. Annikov ◽  
B. N. Kondrikov
Keyword(s):  
Combustion Diameter ◽  
Critical Combustion

Critical combustion diameter of a ballistic powder

1978 ◽  
Vol 14 (1) ◽  
pp. 31-34 ◽  
Author(s):  
A. A. Zenin ◽  
O. I. Leipunskii ◽  
B. V. Novozhilov ◽  
V. M. Puchkov
Keyword(s):  
Ballistic Powder ◽  
Combustion Diameter ◽  
Critical Combustion

Some critical combustion aspects of reformulated heating fuels

Fuel ◽  
1995 ◽  
Vol 74 (2) ◽  
pp. 147-152 ◽  
Author(s):  
S.Win Lee ◽  
David P.C. Fung
Keyword(s):  
Critical Combustion

Assessment of Biofuels/Jet A-1 Blends to Meet Cold Start and Altitude Relight Requirements

2017 ◽  
Author(s):  
Joël Jean ◽  
Alain Fossi ◽  
Alain deChamplain ◽  
Bernard Paquet
Keyword(s):  
Negative Impact ◽  
Cold Start ◽  
Operating Pressure ◽  
Pressure Drops ◽  
Steam Ejector ◽  
Engine Testing ◽  
Almost All ◽  
Engine Components ◽  
Critical Combustion ◽  
Better Than

The certification of new fuels for aircraft applications requires preliminary extensive investigations for the most critical combustion phases. Especially, cold start and altitude relight of an aircraft gas turbine and thus its operating envelope could potentially be affected by the use of new fuels. To assess such effects, a test rig is designed using two different air-assist pressure atomizers. The ignition envelopes for seven different blends with a minimum of 50% Jet A-1 are compared to that of pure Jet A-1. Variation in combustor aerodynamics is accounted for by considering various pressure drops across the combustion chamber, and the ignition envelope is retrieved by finding the minimum and maximum fuel-air ratios leading to a successful ignition event. Effects of fuel physical properties, pressure and temperature which are critical factors for a successful ignition event are also investigated. To simulate cold start and altitude relight, a heat exchanger is used to cool air and fuel, while a bleed valve mounted between the combustor and a steam ejector is used to regulate the operating pressure. Globally, cold start for temperatures ranging from 10°C to −40°C, and the altitude relight for operating altitudes ranging from 4 572 m to 10 668 m, show that the lean limit for the seven blends of fuels are in some cases as good as, and for the other cases better than the pure Jet A-1. Some discrepancies are noted for altitude relight at 9 161 m and 10 688 m, for some biofuels with a minimum of 50% Jet A-1, suggesting a need of real engine testing before final approval. Apart from these isolate cases, almost all the biofuel blends with a minimum of 50% Jet A-1 are truly “drop-in” fuels and should qualify for aviation use since they do not present any negative impact on the typical engine components used in the test program. Furthermore, ASTM D1655 requirements are also achieved for all test conditions. Biofuel blends with less than 50% Jet A-1 are found to always be better than the biofuel blends with minimum of 50% Jet A-1 and, it is recommended to modify ASTM D1655 to include them as acceptable “drop-in” fuels.

Some Basic Studies of Liquid Propellant Injection Processes

1964 ◽  
Vol 68 (647) ◽  
pp. 743-750
Author(s):  
J. D. Lewis
Keyword(s):  
High Speed ◽  
Rocket Engine ◽  
Small Scale ◽  
Performance Measurements ◽  
Liquid Propellant ◽  
Controlling Parameter ◽  
Engine Combustion ◽  
The Subject ◽  
Basic Studies ◽  
Critical Combustion

SummaryThe recent analytical studies of rocket engine combustion based on propellant vaporisation as the rate controlling parameter, especially those by Spalding, and Priem and Heidmann, have contributed greatly to our appreciation of the mechanism of stable combustion. Critical combustion experiments on a small scale engine have shown fair agreement with vaporisation predictions, but have also revealed the need to understand and improve the mixing process.In parallel with performance measurements in a combustion system, detailed measurements of the atomisation process including the break-up mechanism and drop-size distribution have been made. However, there are many gaps in our knowledge of the subject and further work remains to be done.It is thought that the high-speed photographic and gas sampling techniques developed for these investigations provide useful research tools for more detailed studies of the problems.

Sign in / Sign up

Export Citation Format

Share Document