CFD-Led Designs of Pre-Filming Injectors for Gas-Turbine Combustors

2018 ◽  
Author(s):  
Kumud Ajmani ◽  
Hukam Mongia ◽  
Phil Lee ◽  
Kathleen Tacina
Keyword(s):  
Gas Turbine ◽  
Parametric Design ◽  
Direct Injection ◽  
Flow Simulation ◽  
Interaction Model ◽  
Aerodynamic Characteristics ◽  
Reacting Flow ◽  
Gas Turbine Combustors ◽  
Main Injection ◽  
Design Integration

The National Combustion Code (OpenNCC) was used to perform parametric design and analysis for three iterations of pre-filming injector design for gas-turbine combustors. The CFD analysis had significant impact on the design, integration and fabrication of a third-generation Lean-Direct Injection (LDI-3) flame-tube assembly consisting of nineteen injection elements. The air passages of the three pilot elements and sixteen main injection elements consisted of CFD-optimized compound-angle discrete jets and dual axial-bladed swirl-venturi passages, respectively. The aerodynamic characteristics of the nineteen-element injection array were evaluated by performing non-reacting flow simulation using a Time-Filtered Navier-Stokes (TFNS) method. The pilot and main injection elements were fueled with conventional pressure-atomizers and newly designed pre-filming nozzles, respectively. Fuel-air mixing and combustion performance was evaluated with reacting-flow TFNS computations using a 14-species, 18-step reduced kinetics mechanism for Jet-A fuel, Lagrangian spray modeling and a PDF turbulent-chemistry interaction model. The TFNS reacting-flow simulations provided considerable insight into the correlation between aerodynamics, combustion and emissions performance of the newly-designed pilot and main injection elements for the LDI-3 combustor at simulated cruise conditions.

CFD Modeling of Non-Premixed Combustion in a Gas Turbine Combustor

2002 ◽  
Author(s):  
Kitano Majidi
Keyword(s):  
Gas Turbine ◽  
Transport Model ◽  
Direct Injection ◽  
Turbulence Models ◽  
Cfd Modeling ◽  
Navier Stokes ◽  
Reacting Flow ◽  
Gas Temperature ◽  
Gas Turbine Combustor ◽  
Reynolds Stress Transport Model

In the present study numerical calculations are used to solve reacting flow in a gas turbine combustor. A 3-D Favre-Averaged Navier-Stokes solver for a mixture of chemically reacting gases is applied to predict the flow pattern, gas temperature and fuel and species concentrations in the entire combustor. The complete combustor geometry with all important details such as air swirler vane passages and secondary holes are modeled. The calculations are carried out using three different turbulence models. Comparisons are made between the standard k-ε model, RNG k-ε model and a Reynolds stress transport model. To provide a closure for the chemical source term the Eddy Dissipation model is used. A lean direct injection of a liquid fuel is employed. Furthermore the influence of radiation will be investigated.

Numerical and Experimental Analysis of the Temperature Distribution in a Hydrogen Fuelled Combustor for a 10 MW Gas Turbine

2010 ◽  
Vol 133 (2) ◽  
Author(s):  
Massimo Masi ◽  
Paolo Gobbato ◽  
Andrea Toffolo ◽  
Andrea Lazzaretto ◽  
Stefano Cocchi
Keyword(s):  
Temperature Distribution ◽  
Gas Turbine ◽  
High Performance ◽  
Turbine Blades ◽  
Steam Injection ◽  
Operating Conditions ◽  
Injection System ◽  
Reacting Flow ◽  
Cfd Model ◽  
Gas Turbine Combustors

Proper cooling of the hot components and an optimal temperature distribution at the turbine inlet are fundamental targets for gas turbine combustors. In particular, the temperature distribution at the combustor discharge is a critical issue for the durability of the turbine blades and the high performance of the engine. At present, CFD is a widely used tool to simulate the reacting flow inside gas turbine combustors. This paper presents a numerical analysis of a single can type combustor designed to be fed both with hydrogen and natural gas. The combustor also features a steam injection system to restrain the NOx pollutants. The simulations were carried out to quantify the effect of fuel type and steam injection on the temperature field. The CFD model employs a computationally low cost approach, thus the physical domain is meshed with a coarse grid. A full-scale test campaign was performed on the combustor: temperatures at the liner wall and the combustor outlet were acquired at different operating conditions. These experimental data, which are discussed, were used to evaluate the capability of the present CFD model to predict temperature values for combustor operation with different fuels and steam to fuel ratios.

The Premixed Conditional Moment Closure Method Applied to Idealized Lean Premixed Gas Turbine Combustors

2003 ◽  
Vol 125 (4) ◽  
pp. 895-900 ◽  
Author(s):  
S. M. Martin ◽  
J. C. Kramlich ◽  
G. Kosa´ly ◽  
J. J. Riley
Keyword(s):  
Gas Turbine ◽  
Kinetic Mechanism ◽  
Reaction Rates ◽  
Design Tool ◽  
Moment Closure ◽  
Reacting Flow ◽  
Conditional Moment ◽  
Gas Turbine Combustors ◽  
Conditional Moment Closure ◽  
Lean Premixed

This paper presents the premixed conditional moment closure (CMC) method as a new tool for modeling turbulent premixed combustion with detailed chemistry. By using conditional averages the CMC method can more accurately model the affects of the turbulent fluctuations of the temperature on the reaction rates. This provides an improved means of solving a major problem with traditional turbulent reacting flow models, namely how to close the reaction rate source term. Combined with a commercial CFD code this model provides insight into the emission formation pathways with reasonable runtimes. Results using the full GRI2.11 methane kinetic mechanism are compared to experimental data for a backward-facing step burning premixed methane. This model holds promise as a design tool for lean premixed gas turbine combustors.

Numerical and Experimental Analysis of the Temperature Distribution in a Hydrogen Fuelled Combustor for a 10 MW Gas Turbine

2010 ◽  
Author(s):  
Massimo Masi ◽  
Paolo Gobbato ◽  
Andrea Toffolo ◽  
Andrea Lazzaretto ◽  
Stefano Cocchi
Keyword(s):  
Temperature Distribution ◽  
Gas Turbine ◽  
High Performance ◽  
Turbine Blades ◽  
Steam Injection ◽  
Operating Conditions ◽  
Injection System ◽  
Reacting Flow ◽  
Cfd Model ◽  
Gas Turbine Combustors

Proper cooling of the hot components and an optimal temperature distribution at the turbine inlet are fundamental targets for gas turbine combustors. In particular, the temperature distribution at the combustor discharge is a critical issue for the durability of the turbine blades and the high performance of the engine. At present, CFD is a widely used tool to simulate the reacting flow inside gas turbine combustors. This paper presents a numerical analysis of a single can type combustor designed to be fed both with hydrogen and natural gas. The combustor also features a steam injection system to restrain the NOx pollutants. The simulations were carried out to quantify the effect of fuel type and steam injection on the temperature field. The CFD model employs a computationally low cost approach, thus the physical domain is meshed with a coarse grid. A full-scale test campaign was performed on the combustor: temperatures at the liner wall and the combustor outlet were acquired at different operating conditions. These experimental data, which are discussed, were used to evaluate the capability of the present CFD model to predict temperature values for combustor operation with different fuels and steam-fuel ratios.

CFD-Based, Parametric, Design Tool for Gas Turbine Combustors From Compressor Deswirl Exit to Turbine Inlet

2002 ◽  
Author(s):  
Mark K. Lai ◽  
Robert S. Reynolds ◽  
Jeffrey Armstrong
Keyword(s):  
Gas Turbine ◽  
Parametric Design ◽  
Reverse Flow ◽  
Internal Flow ◽  
Setup Time ◽  
Design Tool ◽  
Ease Of Use ◽  
Analysis Tool ◽  
Gas Turbine Combustors ◽  
Through Flow

Since 1998, the Honeywell Engines & Systems, Combustion & Emissions Group has been developing an advanced, CFD-based, parametric, detailed design-by-analysis tool for gas turbine combustors called Advanced Combustion Tools (ACT). ACT solves the entire flow regime from the compressor deswirl exit to the turbine stator inlet, and can be used for combustor diagnostics, design, and development. ACT is applicable to can, through-flow, and reverse-flow combustors, and accommodates features unique to different combustor designs. The main features of ACT are: 1. Reduction of Analysis Cycle Time: Geometry modeling and grid generation are fully parametric and modular, using an inhouse feature-based technology. Each geometrical feature can be deleted, replaced, added, and modified easily, quickly, and efficiently. 2. Elimination of Inter-Feature Boundary Assumptions: All the complex combustor features, such as wall cooling configuration, details of the air swirler assemblies and fuel atomizer systems, dome-shroud/cowl wall, and splash cooling plate, are considered and fully coupled into the CFD calculations. This allows the plenum and annulus aerodynamics to interact directly with the combustor internal flow. 3. Ease of Use: To reduce setup time and errors and to facilitate parametric studies, ACT is highly customized for engineers. 4. Accurate and Efficient CFD Solutions: Advanced physical submodels of combustion and spray have been implemented. This paper provides an overview and development experiences of ACT. Application of ACT to a through-flow combustor system is presented to illustrate the approach as applied to real-world combustors. Validation of the ACT system, by comparison to test cell data, is in-progress and will be the subject of a future paper.

The Premixed Conditional Moment Closure Method Applied to Idealized Lean Premixed Gas Turbine Combustors

2002 ◽  
Author(s):  
Scott M. Martin ◽  
John C. Kramlich ◽  
George Kosa´ly ◽  
James J. Riley
Keyword(s):  
Gas Turbine ◽  
Kinetic Mechanism ◽  
Reaction Rates ◽  
Design Tool ◽  
Moment Closure ◽  
Reacting Flow ◽  
Conditional Moment ◽  
Gas Turbine Combustors ◽  
Conditional Moment Closure ◽  
Lean Premixed

This paper presents the premixed Conditional Moment Closure (CMC) method as a new tool for modeling turbulent premixed combustion with detailed chemistry. By using conditional averages the CMC method can more accurately model the affects of the turbulent fluctuations of the temperature on the reaction rates. This provides an improved means of solving a major problem with traditional turbulent reacting flow models, namely how to close the reaction rate source term. Combined with a commercial CFD code this model provides insight into the emission formation pathways with reasonable runtimes. Results using the full GRI2.11 methane kinetic mechanism are compared to experimental data for a backward facing step burning premixed methane. This model holds promise as a design tool for lean premixed gas turbine combustors.

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