MORE INFORMATION ABOUT THE PROJECT
The detailed design of a combustion chamber that operates efficiently, is not an easy task, which is why this article aims to explain how the simplest methodology of a project of this magnitude.
The Research Center for Aerospace Technology (CITA) requires expand its infrastructure in order to give free rein to the various projects being carried out there is why the research center raises as one of its objectives the acquisition or development of a laboratory combustion for the purpose of allowing students to advance their knowledge in the area of propulsion and combustion specifically the line, in order to be able to evaluate the characteristics of various fuels used in gas turbines.
To help with the work CITA, the detailed design of a combustion chamber complements the future development of the above-mentioned laboratory, in two respects, in terms of academic initiative and leaves footprints to proceed with the completion of the primary objective. That takes a giant step in the production and evaluation of the systems that make up a test bed.
The first step forward in the acquisition of knowledge is the method of analysis because it will identify each one of the most specific that characterize the functioning and operation of the combustion chamber. A continued mentioned basic concepts required to understand the development of the project.
The combustion chamber thermal energy supplied to the engine, which involves the increase of the temperature of the airflow that comes from the compressor (Image 1).
Likewise there are three types of combustion chambers, type override which is the mainstay of this project-type tubular or can and can-type cancel or annul-tube.
The reaction of termoquímico combustion is a process that takes place when a fuel mixture with a oxidizer for the case of the engines oxidizer is the air which has a defined composition that determines the behavior and direction of the reaction (Image 2).
And so Real:
Calculating the estequiométric relation for different fuels including C16H32, C7H16, C12H24, obtaining the best value is estequiométric him of the heptane as shown.
A. Length, L
B. External diameter, De
C. Inner diameter, Di
D. Pressure upon leaving the combustion chamber, P3
E. Temperature at the exit of the combustion chamber T
F. Area cross section AST
G. Reference speed, Vref
H. Lost cargo, Pc
I. Number of moles of products (chemical reaction), Np
J. Number of moles of the reactants (chemical reaction), Nr
K. Enthalpies of formation of the reactants and products, hof
L. Change enthalpy of products and reactants, HT Δ
M. Power, P
N. Dimensions compressor (diameters), D
O. Pressure to the output of the compressor, P2
P. Sue compressor thickness, h
Calculations were done to each respective resulted in the following combustion chamber with their respective dimensions (Image 3).
- Wm = 0.0166m2 Wm defined as Area cross section
Area Primary amount of holes
-- 24 by 2 mm in diameter
-- 24 by 2.5 mm diameter
-- 24 mm diameter by 3
-- 24 by 2 mm in diameter
-- 24 by 2.5 mm diameter
Area amount of dilution holes
-- 12 by 4.5 mm diameter
-- 12 mm diameter by 6
-- 20 mm diameter by 6
-- 12 by 3.5 mm diameter
-- 12 mm diameter by 6
-- 12 by 2.5 mm diameter
All of these holes are distributed evenly in the combustion chamber
-- Number of vaporizers and injectors 10
-- Field steel 304, 0.5mm thick
It was subsequently performed the design of the compressor coupling to be used in the laboratory to get results that are shown in Image 4.
Image 4. Assemble annular combustion chamber - compressor to be used in the laboratory
Finally we can only mention that if you need more information refer to the draft grade "Detailed Design Of A House To Operate From Combustion Efficiency In The Way Of The Combustion Laboratory For CITA" where you find the supplement to the information narrated in this blog or contact me via e-mail carlos.cantor79 @ gmail.com.
The Research Center for Aerospace Technology (CITA) requires expand its infrastructure in order to give free rein to the various projects being carried out there is why the research center raises as one of its objectives the acquisition or development of a laboratory combustion for the purpose of allowing students to advance their knowledge in the area of propulsion and combustion specifically the line, in order to be able to evaluate the characteristics of various fuels used in gas turbines.
To help with the work CITA, the detailed design of a combustion chamber complements the future development of the above-mentioned laboratory, in two respects, in terms of academic initiative and leaves footprints to proceed with the completion of the primary objective. That takes a giant step in the production and evaluation of the systems that make up a test bed.
The first step forward in the acquisition of knowledge is the method of analysis because it will identify each one of the most specific that characterize the functioning and operation of the combustion chamber. A continued mentioned basic concepts required to understand the development of the project.
The combustion chamber thermal energy supplied to the engine, which involves the increase of the temperature of the airflow that comes from the compressor (Image 1).
Image 1. Combustion chamber type override
Likewise there are three types of combustion chambers, type override which is the mainstay of this project-type tubular or can and can-type cancel or annul-tube.
The reaction of termoquímico combustion is a process that takes place when a fuel mixture with a oxidizer for the case of the engines oxidizer is the air which has a defined composition that determines the behavior and direction of the reaction (Image 2).
Image 2. Membership air
Thus would the reaction of combustion would be defined in two ways, an ideal way:
And so Real:Calculating the estequiométric relation for different fuels including C16H32, C7H16, C12H24, obtaining the best value is estequiométric him of the heptane as shown.
Therefore all calculations are developed with this fuel, taking into account its minimum emission of pollutants. After complying with the design parameters for combustion chambers listed below.
A. Length, L
B. External diameter, De
C. Inner diameter, Di
D. Pressure upon leaving the combustion chamber, P3
E. Temperature at the exit of the combustion chamber T
F. Area cross section AST
G. Reference speed, Vref
H. Lost cargo, Pc
I. Number of moles of products (chemical reaction), Np
J. Number of moles of the reactants (chemical reaction), Nr
K. Enthalpies of formation of the reactants and products, hof
L. Change enthalpy of products and reactants, HT Δ
M. Power, P
N. Dimensions compressor (diameters), D
O. Pressure to the output of the compressor, P2
P. Sue compressor thickness, h
Calculations were done to each respective resulted in the following combustion chamber with their respective dimensions (Image 3).
Image 3. Combustion chamber obtained through the calculations of Design Parameters
- Wm = 0.0166m2 Wm defined as Area cross section
Area Primary amount of holes
-- 24 by 2 mm in diameter
-- 24 by 2.5 mm diameter
-- 24 mm diameter by 3
-- 24 by 2 mm in diameter
-- 24 by 2.5 mm diameter
Area amount of dilution holes
-- 12 by 4.5 mm diameter
-- 12 mm diameter by 6
-- 20 mm diameter by 6
-- 12 by 3.5 mm diameter
-- 12 mm diameter by 6
-- 12 by 2.5 mm diameter
All of these holes are distributed evenly in the combustion chamber
-- Number of vaporizers and injectors 10
-- Field steel 304, 0.5mm thick
It was subsequently performed the design of the compressor coupling to be used in the laboratory to get results that are shown in Image 4.
Image 4. Assemble annular combustion chamber - compressor to be used in the laboratory
Finally we can only mention that if you need more information refer to the draft grade "Detailed Design Of A House To Operate From Combustion Efficiency In The Way Of The Combustion Laboratory For CITA" where you find the supplement to the information narrated in this blog or contact me via e-mail carlos.cantor79 @ gmail.com.
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