Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor
-
K. V. L. Narayana Rao
,
B. V. S. S. S. Prasad
Abstract
Experimental and numerical investigations are carried out on an annular, straight flow, swirl-stabilized aero engine combustor. In this work, the effect of degree and direction of swirl at the inlet of combustion chamber is examined on the liner wall temperature and hot spots. This is carried out by experimentally measuring the liner outer wall temperature at discrete positions along the circumferential and axial directions of the combustor liner in the engine test facility. The RANS based turbulence modeling with reacting flow approach is used to simulate the flow domain. Conjugate heat transfer analysis is used to estimate the liner wall temperature using Ansys CFX frame work. The degree and direction of swirl at the inlet of combustion chamber is found to alter the velocity and temperature profiles inside the combustor and hence found to have a significant effect on the liner hot spots and its location. Hotspot with 43 % increase in temperature near the secondary zone is observed with the increase in swirl angle from 5° to 15° at the combustor inlet. The location of the hotspot is found to be dependent on the swirl direction.
Nomenclature
- CCW
-
Counter clock wise direction
- CFD
-
Computational fluid dynamics
- CHT
-
Conjugate Heat transfer
- CPF
-
Circumferential pattern factor
- CW
-
Clock wise direction
- DAS
-
Data acquisition system
- EDM
-
Eddy dissipation model
- FAR
-
Fuel air ratio
- hc
-
convective heat transfer coefficient
- IGV
-
Inlet Guide Vanes
- m
-
Mass flow rate
- max
-
Maximum
- Nu
-
Nusselt Number
- P
-
Pressure
- Pr
-
Prandtl number
- R
-
gas constant
- RANS
-
Reynolds averaged Navier stokes equations
- Re
-
Reynold’s Number
- RMS
-
Root mean square
- SMD
-
Sauter mean diameter
- T
-
Temperature
- RPF
-
Radial pattern factor
- W
-
Molar mass of component I
- y+
-
Non dimensional distance from wall
- Greek Symbols
- θ
-
Angle
- ν
-
Stoichiometric coefficient
- µ
-
Dynamic viscosity
- ν
-
Kinematic viscosity
- Subscripts
- 3
-
Compressor exit or combustor inlet
- 4
-
Combustor exit
- a
-
Air
- c
-
Circumferential
- f
-
Fuel
- L
-
Liner
- I
-
Species component
- t
-
Turbulent
- sw
-
Swirl
- u
-
Universal
Acknowledgements
The authors are thankful to the project management, design, planning and the instrumentation teams for the support during the experimental setup and testing.
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© 2019 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Robust Fault Identification of Turbofan Engines Sensors Based on Fractional-Order Integral Sliding Mode Observer
- A new compilation method of general standard test load spectrum for aircraft engine
- Numerical Investigation on the Effects of Vortex Generator Locations on Film Cooling Performance
- The Effect of the Circumferential Position of Duct Hole on the Non-uniformity in the Axial Compressor
- Surplus Power Approach to Diagnose Gas Turbine Engine Starting Characteristics
- A Flow Dynamic Characteristic Analysis of A Single Radial Swirler Combustor
- Investigation on the Jet Stiffness Characteristics of a Novel Plasma Igniter
- Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor
- Multidisciplinary Design Optimization of the Composite Cooling Structure for Nickel-based Alloy Turbine Blade
- Experimental Study of Non-Premixed Flames of Liquefied Petroleum Gas and Air in Cross-Flow and the Effects of Fuel Properties on Flame Stability
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Robust Fault Identification of Turbofan Engines Sensors Based on Fractional-Order Integral Sliding Mode Observer
- A new compilation method of general standard test load spectrum for aircraft engine
- Numerical Investigation on the Effects of Vortex Generator Locations on Film Cooling Performance
- The Effect of the Circumferential Position of Duct Hole on the Non-uniformity in the Axial Compressor
- Surplus Power Approach to Diagnose Gas Turbine Engine Starting Characteristics
- A Flow Dynamic Characteristic Analysis of A Single Radial Swirler Combustor
- Investigation on the Jet Stiffness Characteristics of a Novel Plasma Igniter
- Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor
- Multidisciplinary Design Optimization of the Composite Cooling Structure for Nickel-based Alloy Turbine Blade
- Experimental Study of Non-Premixed Flames of Liquefied Petroleum Gas and Air in Cross-Flow and the Effects of Fuel Properties on Flame Stability
