Abstract
Gas turbine design is a purposeful activity directed towards the goal of fulfilling the needs of aviation industry. Out of all the components in a gas turbine engine, particularly combustion systems are least amenable. The present chapter shows a design methodology for a “can type” combustor used in airborne engines. The idea is to provide information for producing design for gas turbine combustors such that air staging is required at various locations in the combustor. Various empirical relations were used in the design process. A suitable combustor configuration is selected by calculating the length and diameter of the combustor and the dimensions of the air admission holes at various locations, for secondary air, and quenching air. Pressure measurements were done at the combustor inlet (i.e., at quenching air inlet and primary inlet pipe), in-order to estimate the pressure loss coefficient of the combustion chamber.
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Abbreviations
- I.S.A:
-
International Standard Atmosphere
- \( \dot{m}_{3} \) :
-
Inlet air mass flow rate (unit: kg/s)
- \( \dot{m}_{\text{SW}} \) :
-
Mass flow rate through swirler (unit: kg/s)
- \( \dot{m}_{\text{ZP}} \) :
-
Mass flow rate in primary zone (unit: kg/s)
- \( \dot{m}_{\text{f}} \) :
-
Mass flow rate of fuel (unit: kg/s)
- \( \Delta P_{3 - 4} /P_{3} \) :
-
Combustor pressure loss
- \( \Delta P_{3 - 4} /q_{\text{ref}} \) :
-
Combustor pressure loss factor
- \( \frac{{\Delta P_{\text{SW}} }}{{{\text{q}}_{\text{ref}} }} \) :
-
Pressure loss across swirler
- \( \frac{{\Delta P_{h} }}{{P_{3} }} \) :
-
Pressure loss across holes
- \( A_{\text{ref}} \) :
-
Reference area (unit: m2)
- \( A_{\text{ft}} \) :
-
Cross sectional combustor area (unit: m2)
- \( A_{\text{sw}} \) :
-
Swirler area (unit: m2)
- A h :
-
Area of the hole (unit: m2)
- A an :
-
Area of the annulus (unit: m2)
- \( V_{c} \) :
-
Volume of the combustor (unit: m3)
- C f :
-
Flow coefficient
- C d :
-
Coefficient of discharge of the flow meter
- C v :
-
Coefficient of velocity due to vena-contracta
- \( C_{\text{dh}} \) :
-
Hole discharge coefficient
- \( D_{\text{ref}} \) :
-
Reference diameter (unit: m)
- \( D_{\text{ft}} \) :
-
Combustor diameter (unit: m)
- \( d_{\text{h}} \) :
-
Hole diameter (unit: m)
- \( K_{\text{SW}} \) :
-
Swirler concordance factor
- \( L_{\text{Dz}} \) :
-
Secondary zone length (unit: m)
- \( P_{3} \) :
-
Inlet pressure (unit: P)
- \( R_{a} \) :
-
Specific gas constant (unit: J/Kg−1 K−1)
- R :
-
Outer radius of the swirler (unit: m)
- r :
-
Inner radius of the swirler (unit: m)
- T 3 :
-
Inlet temperature (unit: K)
- T 4 :
-
Exit temperature (unit: K)
- T max :
-
Max exit temperature (unit: K)
- K :
-
Factor of pressure loss
- K1, K2, K3:
-
Empirical constants
- q ref :
-
Reference dynamic pressure (unit: kg/(m s2)
- TQ:
-
Temperature quality factor
- \( M_{c} \) :
-
Air velocity loading parameter
- LHV:
-
Lower heating value (KJ/Kg)
- \( N_{\text{h}} \) :
-
No. of holes
- \( \left( {F/A} \right)_{\text{act}} \) :
-
Fuel to air ratio actual
- \( \left( {F/A} \right)_{\text{St}} \) :
-
Fuel to air ratio stoichiometric
- \( \beta_{\text{SW}} \) :
-
Turning angle of the airflow (unit: °)
- \( \Omega _{c} \) :
-
Air loading parameter
- \( \Omega \) :
-
Non-dimensional efficiency parameter
- \( \phi_{\text{PZ}} \) :
-
Primary zone equivalence ratio
- \( \phi_{\text{global}} \) :
-
Global equivalence ratio
- α:
-
Orifice area ratio
- μ:
-
Bleed to orifice area ratio
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Roshan, D.K., Burela, R.S., Kushari, A. (2020). Design Philosophy for a Laboratory Scale Gas Turbine Combustor. In: Gupta, A., De, A., Aggarwal, S., Kushari, A., Runchal, A. (eds) Innovations in Sustainable Energy and Cleaner Environment. Green Energy and Technology. Springer, Singapore. https://doi.org/10.1007/978-981-13-9012-8_14
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