Design and Validation of a Burner With Variable Geometry for Extended Combustion Range

A study on innovative gas turbine core concepts supported by the NEWAC project (NEW Aero-engine Core concepts, Integrated Project co-funded by the European Commission within the Sixth Framework Programme under contract No. AIP5-CT-2006-030876) focused on the ability of the combustor to maintain combustion during a drastic reduction of the main air, e.g. due to an active control on the core flow to improve the off-design efficiency. A feasibility study was performed at Graz University of Technology including dimensioning, design and validation of a test burner with variable geometry. A low power premixed methane / air burner with swirl-stabilised flame was chosen, on which the outlet surface and the ratio axial to tangential momentum on the mass flow rate could be controlled. During testing at atmospheric conditions, special attention was paid to the extension of the flammability domain and to the flame dynamics (transition attached-detached, flame stability, blowout limits). It was established for instance that based on this technology, a detached flame can be maintained when reducing the design mass flow rate by 40 per cent within a safe stability range. The paper discusses the background of the study, the burner’s design and technology, the measurement techniques and the results of the validation campaign. A discussion on possible advantages of using variable geometry in a combustion chamber versus conventional technologies closes the paper, taking into account the technical challenges to be met.

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A physics-based turbocharger model for automotive diesel engine control applications

Proceedings of the Institution of Mechanical Engineers Part D Journal of Automobile Engineering ◽

10.1177/0954407018770569 ◽

2018 ◽

Vol 233 (7) ◽

pp. 1667-1686 ◽

Cited By ~ 2

Author(s):

Kang Song ◽

Devesh Upadhyay ◽

Hui Xie

Keyword(s):

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Turbine Rotor ◽

Variable Geometry ◽

Gas Velocity ◽

Euler’S Equations ◽

Variable Geometry Turbine ◽

Euler's Equations ◽

Compressor Power

Control-oriented models of turbocharger processes such as the compressor mass flow rate, the compressor power, and the variable geometry turbine power are presented. In a departure from approaches that rely on ad hoc empirical relationships and/or supplier provided performance maps, models based on turbomachinery physics and known geometries are attempted. The compressor power model is developed using Euler’s equations of turbomachinery, where the gas velocity exiting the rotor is estimated from an empirically identified correlation for the ratio between the radial and tangential components of the gas velocity. The compressor mass flow rate is modeled based on mass conservation, by approximating the compressor as an adiabatic converging-diverging nozzle with compressible fluid driven by external work input from the compressor wheel. The variable geometry turbine power is developed with Euler’s equations, where the turbine exit swirl and the gas acceleration in the vaneless space are neglected. The gas flow direction into the turbine rotor is assumed to align with the orientation of the variable geometry turbine vane. The gas exit velocity is calculated, similar to the compressor, based on an empirical model for the ratio between the turbine rotor inlet and exit velocities. A power loss model is also proposed that allows proper accounting of power transfer between the turbine and compressor. Model validation against experimental data is presented.

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Development of Turbine Mass Flow Rate Model for Variable Geometry Turbocharger Using Artificial Neural Network

Transactions of the Korean Society of Mechanical Engineers B ◽

10.3795/ksme-b.2010.34.8.783 ◽

2010 ◽

Vol 34 (8) ◽

pp. 783-790 ◽

Cited By ~ 5

Author(s):

Yeong-Seop Park ◽

Byoung-Gul Oh ◽

Min-Kwang Lee ◽

Myoung-Ho SunWoo

Keyword(s):

Neural Network ◽

Artificial Neural Network ◽

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Variable Geometry ◽

Rate Model ◽

Variable Geometry Turbocharger ◽

Artificial Neural

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Gas Turbine Tubular Combustor Main Injector Optimization for Low Emission Combustion

Journal of University of Babylon for Engineering Sciences ◽

10.29196/jubes.v26i10.1799 ◽

2018 ◽

Vol 26 (10) ◽

pp. 1-12

Author(s):

Arkan Khikhal Husain ◽

Mahmood Attallah Mashkoor ◽

Fuad Abdul Ameer Khalaf

Keyword(s):

Gas Turbine ◽

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

High Performance ◽

Atmospheric Conditions ◽

Air Mass ◽

Fuel Flow ◽

Low Emission ◽

Gas Fuel

This work presents the experimental investigation results of high performance and low emission colorless combustion in a gas turbine tubular combustor at atmospheric conditions. Low emission and colorless oxidation reaction is characterized by dispersed flame and temperature under the conditions of preheated air. System performance, emissions of CO and UHC are recorded up to achieve low emission colorless combustion, the flame capturing, Measurements of temperature, inlet air mass flow rate and gas fuel LPG flow rate for variable of fuel main injector holes diameter. concluded that maximal air mass flow rate, with choked fuel flow in the main injector for each cases promotes the formation of colorless pal blue flame combustion, for 3.2 g/s of fuel flow rate with 6 holes and 1mm main injector holes diameter and lower CO emissions and decreasing in UHC emissions (70 → 10) ppmv with increasing in power generation (0.5 → 3.42) kW and decreasing in S.F.C. (21.5 → 3.49) kg/kwh.

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Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet for TBCC

International Journal of Turbo and Jet Engines ◽

10.1515/tjeng-2020-0030 ◽

2021 ◽

Vol 0 (0) ◽

Author(s):

Yunfei Wang ◽

Huacheng Yuan ◽

Jinsheng Zhang ◽

Zhenggui Zhou

Keyword(s):

Mach Number ◽

Performance Analysis ◽

Mass Flow Rate ◽

Mass Flow ◽

Flow Rate ◽

Design Method ◽

Aerodynamic Performance ◽

Combined Cycle ◽

Variable Geometry

Abstract Design and aerodynamic performance analysis of a variable geometry axisymmetric inlet was carried out for tandem scheme turbine-based combined cycle (TBCC) propulsion system. The operation Mach number of the inlet was between 0 and 4. The design point was chosen as Mach number 4.0 in this paper. The determination of external and internal compression and the design method of annular to circle diffuser were illustrated. The inlet was unstart under Ma 3.0 without adjustment. Then, a variable scheme was designed to ensure self-start of the inlet and match the requirement of mass flow rate during the whole flight envelope. And four supports were used to fix the spike. According to the 3D numerical simulations, the total pressure recovery was 0.52 at Ma 4.0 at critical condition and the mass flow rate was consistent with the requirement at different flight Mach number.

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