Simulation of thermal radiation emitted by heterogeneous combustion products in the combustion chamber of a model engine

Abstract The present paper reports on the investigation of unsteady combustion of a methane-air mixture, including combustion at increased pressure in the combustion chamber and increased temperature of mixture heating for a model gas-turbine swirl burner based on a design by Turbomeca. To measure the velocity and OH fluorescence fields in the flows a combination of stereoscopic PIV and acetone PLIF systems is used. In all cases, the flow dynamics is associated with the movement of large-scale vortex structures in the inner and outer mixing layers and the flow structure corresponds to a swirling jet with a central recirculation zone containing combustion products. An increase in the heating temperature of the mixture and pressure in the combustion chamber leads to a periodic partial separation of the flame from the model swirl nozzle. However, the flow of fuel through the central channel will stabilize the flame.

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Simulation of Pollutant Emissions in a Small-Sized Combustion Chamber With a Gas Fuel for Various Regime Modes

Volume 2: Combustion, Fuels, and Emissions; Renewable Energy: Solar and Wind; Inlets and Exhausts; Emerging Technologies: Hybrid Electric Propulsion and Alternate Power Generation; GT Operation and Maintenance; Materials and Manufacturing (Including Coatings, Composites, CMCs, Additive Manufacturing); Analytics and Digital Solutions for Gas Turbines/Rotating Machinery ◽

10.1115/gtindia2019-2687 ◽

2019 ◽

Author(s):

Nikita I. Gurakov ◽

Ivan A. Zubrilin ◽

Ivan V. Chechet ◽

Vladislav M. Anisimov ◽

Sergey S. Matveev ◽

...

Keyword(s):

Experimental Data ◽

Combustion Chamber ◽

Equivalence Ratio ◽

Stokes Equations ◽

Three Dimensional ◽

Combustion Products ◽

Pollutant Emissions ◽

Eddy Simulation ◽

Flamelet Generated Manifold ◽

Combustion Processes

Abstract The study shows the results of the emission simulation in a small-sized combustion chamber. The influence of temperature and equivalence ratio on CO and CxHy in the combustion chamber was investigated. Experiments and calculations were carried out for the following modes: temperature at the inlet of the combustion chamber Tinlet = 323 ... 523 K; equivalence ratio φ = 0.2 ... 0.33; normalized flow rate at the inlet of the combustion chamber λ = 0.1 ... 0.3. The simulation of combustion of natural gas was carried out. The studies were conducted using CFD software and experimental methods. Measurements of the combustion products composition were carried out by the method of sampling collection and subsequent chromatographic analysis. The flow and combustion processes were simulated in a three-dimensional steady formulation using the Reynolds-averaged Novier-Stokes equations (RANS) and in a transient formulation using the Large Eddy Simulation (LES) method. The combustion processes were simulated by Flamelet Generated Manifold model in conjunction with the probability density function method (PDF). In addition to the above methods, the method of the reactor network model (RNM) was used to simulate the emission. As a result, a comparison of the calculated and experimental data of concentrations values of combustion products and emissions indices averaged over the combustion chamber outlet was conducted. According to the results of the calculated-experimental study obtained: - the simulated concentrations values of the main combustion products such as CO2 and H2O qualitatively and quantitatively coincide with the experimental data (the discrepancy is less than 5%) for all three approaches — RANS, LES, RNM; - when modeling CO emissions, the discrepancy between the calculated emission indices obtained by the RANS and LES methods is greatly underestimated relative to the experimental data, whereas the values calculated by the RNM method deviate from the experiment by less than 10%; - mass concentration values of unburned hydrocarbons obtained by the RANS method are overestimated relative to the experimental values, while using the LES with RNM methods, the discrepancy does not exceed 10%.

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Modeling of thermal radiation of combustion products in the gas generator

2017 International Conference on Industrial Engineering, Applications and Manufacturing (ICIEAM) ◽

10.1109/icieam.2017.8076461 ◽

2017 ◽

Author(s):

V. A. Kuzmin ◽

I. A. Zagrai ◽

N. A. Shmakova

Keyword(s):

Thermal Radiation ◽

Combustion Products ◽

Gas Generator

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Application of Noncircular Primary-Air Inlet Geometries in the Inshot Burners of Residential Gas Furnaces

Journal of Energy Resources Technology ◽

10.1115/1.2792694 ◽

1996 ◽

Vol 118 (1) ◽

pp. 58-64 ◽

Cited By ~ 7

Author(s):

P. Kolluri ◽

A. Kamal ◽

S. R. Gollahalli

Keyword(s):

Temperature Field ◽

Natural Gas ◽

Combustion Chamber ◽

Field Measurements ◽

Air Entrainment ◽

Combustion Products ◽

Nox Emission ◽

Air Inlet ◽

Emission Index

Experiments with an inshot burner used in residential natural gas furnaces are presented. The concentrations of NOx, NO, and CO in the combustion products of partially aerated natural gas flames were measured in a laboratory combustion chamber. When the conventional circular venturi inlet of the inshot burner was replaced by elliptic venturi inlets, an increase of up to 30 percent in the primary-air entrainment and a decrease of up to 20 percent in the NOx emission index were observed. Temperature field measurements in the flames were in conformity with the emission index measurements.

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Selection of temperature and power parameters for multi-modular lunar jet penetrator

INCAS BULLETIN ◽

10.13111/2066-8201.2019.11.s.23 ◽

2019 ◽

Vol 11 (S) ◽

pp. 231-241

Author(s):

Vladimir А. ZAGOVORCHEV ◽

Olga V. TUSHAVINA

Keyword(s):

Combustion Chamber ◽

Modular Design ◽

Combustion Products ◽

Design Parameters ◽

Rocket Engines ◽

Depth Of Penetration ◽

Critical Temperatures ◽

Operation Process ◽

Solid Propellant Rocket ◽

Structural Mass

The questions and the particularity of the choice of design parameters of multi-module lunar jet penetrators are considered. A constructive layout of the penetrator is proposed and the advantages of a multi-modular design are presented. In particular, the limitation on the depth of penetration of the reactive penetrator of the standard scheme, associated with the characteristics of the flow of combustion products from the nozzle into a variable length channel left after the passage of the apparatus, is described. An algorithm is suggested for solving the problem of design parameters of multi-module lunar jet penetrators, which is based on the same methods for finding design parameters of single-module penetrators. Nonetheless, in this case, among the main design parameters that uniquely determine the appearance of both individual modules and the apparatus as a whole, in addition to pressure in the combustion chamber, elongation, pressure relationships at the nozzle and in the chamber, engine running time in air, structural mass and angle, contents of the head including, multiple modules (or sections of the remote control) of the device. By the above method, the calculation of the gas-dynamic parameters for the operation process in solid propellant rocket engines was carried out. Critical temperatures of solid fuel and pressure in the combustion chamber are limited by the ones leading to destruction of the engine and the penetrator.

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

VESTNIK of the Samara State Aerospace University ◽

10.18287/2541-7533-2019-18-1-78-87 ◽

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.

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