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How are the combustion chamber length and diameter decided
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How are the combustion chamber length and diameter decided?
Are there any proper formulations or procedures?
propulsion engine-design combustion combustion-chamber
asked 7 hours ago
Amar
778319
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up vote
4
down vote
favorite
How are the combustion chamber length and diameter decided?
Are there any proper formulations or procedures?
propulsion engine-design combustion combustion-chamber
asked 7 hours ago
Amar
778319
add a comment |Â
up vote
4
down vote
favorite
up vote
4
down vote
favorite
How are the combustion chamber length and diameter decided?
Are there any proper formulations or procedures?
propulsion engine-design combustion combustion-chamber
asked 7 hours ago
Amar
778319
How are the combustion chamber length and diameter decided?
Are there any proper formulations or procedures?
propulsion engine-design combustion combustion-chamber
propulsion engine-design combustion combustion-chamber
asked 7 hours ago
Amar
778319
asked 7 hours ago
Amar
778319
asked 7 hours ago
Amar
778319
asked 7 hours ago
Amar
778319
asked 7 hours ago
Amar
778319
778319
add a comment |Â
add a comment |Â
1 Answer
1
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oldest
votes
up vote
4
down vote
You can referthis book Modern Engineering for Design of Liquid-Propellant Rocket Engines chapter 4.
It depends the on the number of performance parameters such as $C_f, C^*$ and $I_sp$. From which the Throat area is calculated.
Throat area is usually used as a starting point to have the thrust chamber dimensions. Characteristic length and Contraction ratio are the important parameters to have the length and diameter of the chamber.
You can get the contraction ratio for given propellants and throat area from the plot in the book. Chapter 4. Fig 4-9(Refer book Pg 73). Also, a range of characteristic length for different propellants are given in the table 4-1(Refer book Pg 72).
$L^* = fracVcAt = fracW_tc v t_sA_t$
where $V_c$ = chamber volume, $ft$;
$W_tc$ = propellant mass flowrate, $fraclbs$;
$V$ = average specific volume; and
$t_s$ = propellant stay-time, s.
$fracA_cA_t$ is contraction ratio,
where $A_c$ is cross-sectional area of the chamber.
$L^*$ is basically a function of residence time of propellants which can be obtained only by experiments.
Also, Contraction ratio and $L^*$ will not exceed a range as exceeding it will result in significant pressure losses in the chamber.
edited 46 mins ago
Amar
778319
answered 3 hours ago
Vasanth C
18111
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
add a comment |Â
1 Answer
1
active
oldest
votes
1 Answer
1
active
oldest
votes
active
oldest
votes
active
oldest
votes
up vote
4
down vote
You can referthis book Modern Engineering for Design of Liquid-Propellant Rocket Engines chapter 4.
It depends the on the number of performance parameters such as $C_f, C^*$ and $I_sp$. From which the Throat area is calculated.
Throat area is usually used as a starting point to have the thrust chamber dimensions. Characteristic length and Contraction ratio are the important parameters to have the length and diameter of the chamber.
You can get the contraction ratio for given propellants and throat area from the plot in the book. Chapter 4. Fig 4-9(Refer book Pg 73). Also, a range of characteristic length for different propellants are given in the table 4-1(Refer book Pg 72).
$L^* = fracVcAt = fracW_tc v t_sA_t$
where $V_c$ = chamber volume, $ft$;
$W_tc$ = propellant mass flowrate, $fraclbs$;
$V$ = average specific volume; and
$t_s$ = propellant stay-time, s.
$fracA_cA_t$ is contraction ratio,
where $A_c$ is cross-sectional area of the chamber.
$L^*$ is basically a function of residence time of propellants which can be obtained only by experiments.
Also, Contraction ratio and $L^*$ will not exceed a range as exceeding it will result in significant pressure losses in the chamber.
edited 46 mins ago
Amar
778319
answered 3 hours ago
Vasanth C
18111
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
add a comment |Â
up vote
4
down vote
You can referthis book Modern Engineering for Design of Liquid-Propellant Rocket Engines chapter 4.
It depends the on the number of performance parameters such as $C_f, C^*$ and $I_sp$. From which the Throat area is calculated.
Throat area is usually used as a starting point to have the thrust chamber dimensions. Characteristic length and Contraction ratio are the important parameters to have the length and diameter of the chamber.
You can get the contraction ratio for given propellants and throat area from the plot in the book. Chapter 4. Fig 4-9(Refer book Pg 73). Also, a range of characteristic length for different propellants are given in the table 4-1(Refer book Pg 72).
$L^* = fracVcAt = fracW_tc v t_sA_t$
where $V_c$ = chamber volume, $ft$;
$W_tc$ = propellant mass flowrate, $fraclbs$;
$V$ = average specific volume; and
$t_s$ = propellant stay-time, s.
$fracA_cA_t$ is contraction ratio,
where $A_c$ is cross-sectional area of the chamber.
$L^*$ is basically a function of residence time of propellants which can be obtained only by experiments.
Also, Contraction ratio and $L^*$ will not exceed a range as exceeding it will result in significant pressure losses in the chamber.
edited 46 mins ago
Amar
778319
answered 3 hours ago
Vasanth C
18111
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
add a comment |Â
up vote
4
down vote
up vote
4
down vote
You can referthis book Modern Engineering for Design of Liquid-Propellant Rocket Engines chapter 4.
It depends the on the number of performance parameters such as $C_f, C^*$ and $I_sp$. From which the Throat area is calculated.
Throat area is usually used as a starting point to have the thrust chamber dimensions. Characteristic length and Contraction ratio are the important parameters to have the length and diameter of the chamber.
You can get the contraction ratio for given propellants and throat area from the plot in the book. Chapter 4. Fig 4-9(Refer book Pg 73). Also, a range of characteristic length for different propellants are given in the table 4-1(Refer book Pg 72).
$L^* = fracVcAt = fracW_tc v t_sA_t$
where $V_c$ = chamber volume, $ft$;
$W_tc$ = propellant mass flowrate, $fraclbs$;
$V$ = average specific volume; and
$t_s$ = propellant stay-time, s.
$fracA_cA_t$ is contraction ratio,
where $A_c$ is cross-sectional area of the chamber.
$L^*$ is basically a function of residence time of propellants which can be obtained only by experiments.
Also, Contraction ratio and $L^*$ will not exceed a range as exceeding it will result in significant pressure losses in the chamber.
edited 46 mins ago
Amar
778319
answered 3 hours ago
Vasanth C
18111
You can referthis book Modern Engineering for Design of Liquid-Propellant Rocket Engines chapter 4.
It depends the on the number of performance parameters such as $C_f, C^*$ and $I_sp$. From which the Throat area is calculated.
Throat area is usually used as a starting point to have the thrust chamber dimensions. Characteristic length and Contraction ratio are the important parameters to have the length and diameter of the chamber.
You can get the contraction ratio for given propellants and throat area from the plot in the book. Chapter 4. Fig 4-9(Refer book Pg 73). Also, a range of characteristic length for different propellants are given in the table 4-1(Refer book Pg 72).
$L^* = fracVcAt = fracW_tc v t_sA_t$
where $V_c$ = chamber volume, $ft$;
$W_tc$ = propellant mass flowrate, $fraclbs$;
$V$ = average specific volume; and
$t_s$ = propellant stay-time, s.
$fracA_cA_t$ is contraction ratio,
where $A_c$ is cross-sectional area of the chamber.
$L^*$ is basically a function of residence time of propellants which can be obtained only by experiments.
Also, Contraction ratio and $L^*$ will not exceed a range as exceeding it will result in significant pressure losses in the chamber.
edited 46 mins ago
Amar
778319
answered 3 hours ago
Vasanth C
18111
edited 46 mins ago
Amar
778319
edited 46 mins ago
Amar
778319
edited 46 mins ago
Amar
778319
778319
answered 3 hours ago
Vasanth C
18111
answered 3 hours ago
Vasanth C
18111
answered 3 hours ago
Vasanth C
18111
18111
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
add a comment |Â
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
can you tell me the range for $L^*$?
– Amar
3 hours ago
can you tell me the range for $L^*$?
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
I think I got it. I will add it in the answer for you this time.
– Amar
3 hours ago
add a comment |Â
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