Some factors affecting unburned hydrocarbons in engine combustion products

1958 ◽  
Author(s):  
J. N. Shinn ◽  
D. R. Olson
Keyword(s):  
Combustion Products ◽  
Factors Affecting ◽  
Engine Combustion ◽  
Unburned Hydrocarbons

Factors Affecting the Primary Combustion Products of Boron-Based Fuel-Rich Propellants

2017 ◽  
Vol 33 (2) ◽  
pp. 333-337 ◽  
Author(s):  
Lin-lin Liu ◽  
Guo-Qiang He ◽  
Ying-Hong Wang ◽  
Song-Qi Hu ◽  
Yuan-Min Liu
Keyword(s):  
Combustion Products ◽  
Factors Affecting ◽  
Primary Combustion Products

Continuous Measurement of Exhaust Emissions From a High Pressure Cannular Combustor

1972 ◽  
Author(s):  
H. Shaw ◽  
W. F. Taylor ◽  
C. J. McCoy ◽  
A. Skopp
Keyword(s):  
High Pressure ◽  
Equivalence Ratio ◽  
Continuous Measurement ◽  
Combustion Products ◽  
Turbine Engines ◽  
Sampling System ◽  
Engine Emissions ◽  
Turbine Engine ◽  
Unburned Hydrocarbons ◽  
Good Agreement

A high pressure cannular combustor has been developed to simulate aircraft turbine engine emissions. In conjunction with this combustor, a continuous analytical and sampling system was assembled. This system is capable of complete on-the-spot analysis of CO2, O2, CO, H2O, unburned hydrocarbons, and NOx. The measured emission levels obtained from burning Jet A are in good agreement with those reported from operating aircraft turbine engines. Data showing the effect of equivalence ratio and pressure on the concentration of combustion products are presented.

Study of unknown combustion products produced by SI engine combustion using n-heptane as fuel

2021 ◽  
Vol 2021.27 (0) ◽  
pp. 11D12
Author(s):  
Fumiya KAWASHIMA ◽  
Kousuke MONZEN ◽  
Hironobu KOIKE ◽  
Michio NAKANO
Keyword(s):  
Combustion Products ◽  
Si Engine ◽  
Engine Combustion

scholarly journals Development of blend composition of aviation kerosene surrogate for the simulation of workflow of gas turbine engine combustion chamber

2019 ◽  
Vol 18 (1) ◽  
pp. 78-87
Author(s):  
S. G. Matveev
Keyword(s):  
Physicochemical Properties ◽  
Combustion Chamber ◽  
Flow Characteristics ◽  
Combustion Products ◽  
Spray Angle ◽  
Chemical Components ◽  
Turbine Engine ◽  
Aviation Kerosene ◽  
Engine Combustion ◽  
Fuel Nozzle

In this paper, the criteria for determining the composition and physicochemical properties of aviation kerosene were formulated. The data on the physicochemical properties of known kerosene surrogates were systematized and classified. The main classes of individual chemical components of aviation kerosene were determined, and the main representatives of these classes which were used in the preparation of surrogates, were investigated. Four- and six-component kerosene substitutes are proposed. The physical properties of the developed surrogates were validated according to the flow characteristics and the spray angle of the flame of a centrifugal fuel nozzle. The dependence of the flame speed on the composition of the mixture of developed kerosene surrogates was determined. The results of determining the composition of combustion products during the combustion of TS-1 brand aviation kerosene and its surrogates in a model combustion chamber were compared.

scholarly journals Method of Calculating Carbon Ablation in the Jet of Liquid Rocket Engine Combustion Products

2019 ◽  
pp. 4-21
Author(s):  
V.V. Gorskiy ◽  
M.G. Kovalsky ◽  
V.G. Resh
Keyword(s):  
High Pressure ◽  
Carbon Materials ◽  
Thermal Protection ◽  
Rocket Engine ◽  
Combustion Products ◽  
Liquid Rocket Engine ◽  
Experimental Development ◽  
Engine Combustion ◽  
Material Erosion ◽  
Liquid Rocket

Nowadays carbon materials are widely used as ablating thermal protection for high-temperature structural elements in aerospace technology. Prediction of changes in the shape of the external surfaces of these elements, due to the burning of thermal protection, is closely related to the use of computational-theoretical methods describing the flow of various physicochemical and mechanical processes associated with the occurrence of the phenomenon under consideration. At the same time, it is crucial to test such methods on the results of experimental studies conducted under conditions which are implemented during the process of testing thermal protection in jets of aerodynamic units. The main elements of ablation of carbon materials include their erosion, i.e., mechanical ablation of mass, observed in high-pressure gas flows. In the process of experimental development, it is necessary to carry out research on large-scale models, which has led to widespread use of underexpanded jets of combustion products of liquid rocket engine combustion products for modeling the erosion process of thermal protection. The theoretical model of ablation of thermal protection in such jets requires taking into account the complex chemical composition of the gas mixture flowing into the model; physical and chemical interaction of this gas with thermal protection, which causes gasification of the latter; use of mathematical models describing the process of material erosion due to mechanical impact of high-pressure gas flow. The paper describes the development of the carbon material ablation calculating and theoretical methodology which could be used to determine the material erosion characteristics on the basis of solving a complex problem of circumfluence, heating, heat penetration and ablation of thermal protection.

scholarly journals Heat Release Analysis of The Scaled and Colliding Sprays Using RANS Approach

2020 ◽  
Author(s):  
Masumeh Gholamisheeri ◽  
Daniel Norling ◽  
Thomas Hällqvist
Keyword(s):  
Heat Release ◽  
Navier Stokes ◽  
Cross Sectional ◽  
Complete Combustion ◽  
Advantages And Disadvantages ◽  
Engine Combustion ◽  
Constant Volume Combustion Chamber ◽  
Release Analysis ◽  
Unburned Hydrocarbons ◽  
Burn Rate

This study tries to optimize the heat release rate of a diesel injector that is injecting into a constant volume combustion chamber. This optimization is performed via spray scaling through Reynolds Averaged Navier-stokes simulations (RANS). The spray-A (diesel spray from Engine Combustion Network) has been used as a reference for validation of the simulations. To scale the diesel jet, the injected mass and cross-sectional area of the injector are varied with similar scaling factor. It was found that using a larger injector leads to a longer spray penetration, ignition delay, and burn duration while it helps a more complete combustion. On the other hand, using a smaller orifice improves the burn duration and reduces the heat release, while it causes a slightly higher amounts of unburned hydrocarbons. It was revealed that it is reasonable to use multiple smaller orifices (two half size or four quarter size injectors) in place of one single injector, to improve the burn rate. To achieve a complete combustion, the configuration must be tuned. For clarity, three configurations are considered, parallel, non-coaxial colliding and co-axial colliding sprays for which the distance between the sprays and the inclination of the sprays are varied and tested. The advantages and disadvantages of each configuration is discussed in length.

A discussion on advanced methods of energy conversion- Magnetohydrodynamic power generation - Air heaters and seed recovery for m.h.d. plant

1967 ◽  
Vol 261 (1123) ◽  
pp. 514-540 ◽  
Keyword(s):  
Power Generation ◽  
High Temperature ◽  
Fossil Fuels ◽  
Flame Temperature ◽  
Combustion Products ◽  
Design Data ◽  
Factors Affecting ◽  
Model Studies ◽  
Recovery Processes ◽  
Novel Concept

The only economic way of producing sufficiently high flame temperature for m.h.d. power generation using fossil fuels is to burn them with air preheated to at least 1200° C. The factors affecting the design of suitable air heaters for the high temperature stage of this process will be discussed and the features of three general types will be described. One of these is a completely novel concept in which a circulating stream of molten material is used to transfer heat between hot combustion products and air. Experiments which are being carried out to provide design data for these three types will be described and cover the pumping and atomization of high temperature fluids; the testing of suitable refractory materials; aerodynamic model studies; the development of refractory seals. Seeding chemicals introduced to enhance gas conductivity pose special problems of corrosion and deposition in the air heaters and investigations into the interdependent processes of heat and mass transfer will be described. Since the seed cannot be allowed to escape from the system, studies of recovery processes will be referred to in the paper.

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