Advanced User-Friendly Gas Turbine Performance Calculations on a Personal Computer

Kurzke, Joachim

doi:10.1115/95-gt-147

Cited by 51 publications

(31 citation statements)

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“…However, a reduction of life span due to frequent acceleration and deceleration shouldn't be underestimated. Off design and transient analysis of a 50KW turbogenerator gas turbine were performed accordingly to predict the operating characteristics therein using commercially available gas turbine performance analysis code (Kurzke 1995). Figure 1 shows a small turbogenerator gas turbine engine, often found in the open literatures, consisting of a compressor, permanent magnetic generator, turbine and combustor with a recuperator to recover the exhaust heat from the combustor.…”

Section: Introductionmentioning

confidence: 99%

Performance Analysis of a 50KW Turbogenerator Gas Turbine Engine

Kim

Park

Cho

1998

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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This paper describes on/off design performance of a 50KW turbogenerator gas turbine engine for hybrid vehicle application. For optimum design point selection, a relevant pa4rameter study is carried out. The turbogenerator gas turbine engine for a hybrid vehicle is expected to be designed for maximum fuel economy, ultra low emissions, and very low cost. A compressor, combustor, turbine, and a permanent-magnet generator will be mounted on a single high speed (80,000 rpm) shaft that will be supported on air bearings. As the generator is built into the shaft, gearbox and other moving parts become unnecessary and thus will increase the system’s reliability and reduce the manufacturing cost. The engine has a radial compressor and turbine with design point pressure ratio of 4.0. This pressure ratio was set based on calculation of specific fuel consumption and specific power variation with pressure ratio. For the turbine inlet temperature, a rather conservative value of 1100K was selected. Designed mass flow rate was 0.5 kg/sec. Parametric study of the cycle indicates that specific work and efficiency increase at a given pressure ratio and turbine inlet temperature. Off design analysis shows that the gas turbine system reaches self operating condition at about N/NDP = 0.48. Bleeding air for a turbine stator cooling is omitted considering the low TIT in the present engine and to enable the simple geometric configuration for manufacturing purpose. Various engine performance simulations including ambient temperature influence, surging at part load condition; transient analysis were performed to secure the optimum engine operating characteristics. Surge margin throughout the performance analysis were maintained to be over 50% approximately. Present analysis will be compared with performance test result which is scheduled at the end of 1998.

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Section: Introductionmentioning

confidence: 99%

Performance Analysis of a 50KW Turbogenerator Gas Turbine Engine

Kim

Park

Cho

1998

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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“…To extend the test rig performance, the experimental data were compared with predictions obtained by the gas turbine process simulation code GasTurbll by J. Kurzke [16]. For the present study the entry-level version considering the turboshaft engine on a test bed was used for the simple cycle analysis.…”

Section: Modeling and Simulation Of Simple Cyclementioning

confidence: 99%

A Mobile Test Rig for Micro Gas Turbines Based on a Thermal Power Measurement Approach

Wiesche

2012

Journal of Engineering for Gas Turbines and Power

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t is widely considered that micro gas turbines are potential devices for future energy needs. However, many micro gas turbine development projects have failed, particularly those with a very low power level below lOkW. The financial and experimental capabilities for micro gas turbitie development projects are typically extremely limited: hence, there is a need for low cost mobile test rigs. To close this gap, a robust mobile test rig for turboshaft micro gas turbines was developed and validated. The shaft power can be determined using a thermal measurement approach. This circumvents any issues associated with high voltage and electric current levels. The shaft power can be obtained by a straightforward parameter identification procedure based on simple temperature measurements. This approach is feasible became an analytical expression for the transient temperature field can be obtained. The test rig and thermal power measurement concept were fully validated by a commercial micro gas turbine; good agreement was obtained between the experimental results and the theoretical process data.

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“…This tool uses BFTA type maps [47] to describe conventional compressor offdesign performance through tables of pressure ratio (PR), isentropic efficiency (eff), and corrected mass flow rate (Wc) for different values of relative corrected rotational speed (NcRdes) and BFTA (an auxiliary map coordinate). There is also a table of surge pressure ratio (PRsurge) against Wc.…”

Section: Component Mapsmentioning

confidence: 99%

Modeling Contra-Rotating Turbomachinery Components for Engine Performance Simulations: The Geared Turbofan With Contra-Rotating Core Case

Alexiou¹,

Roumeliotis²,

Aretakis³

et al. 2012

Journal of Engineering for Gas Turbines and Power

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This paper presents a method of modeling contra-rotating turbomachinery components for engine performance simulations. The first step is to generate the performance characteristics of such components. In this study, suitably modified one-dimensional mean line codes are used. The characteristics are then converted to three-dimetisional tables (maps). Compared to conventional turbomachinery component maps, the speed ratio between the two shafts is included as an additional map parameter and the torque ratio as an additional table. Dedicated component models are then developed that use these maps to simulate design and off-design operation at the component and engine levels. Using this approach, a performance model of a geared turbofan with a contra-rotating core (CRC) is created. This configuration was investigated in the context of the European program "NEW Aero-Engine Core Concepts" (NEWAC). The core consists of a sevenstage compressor and a two-stage turbine without interstage stators and with successive rotors running in the opposite direction through the introduction of a rotating outer spool. Such a configuration results in a reduced parts count, length, weight, and cost of the entire high pressure (HP) system. Additionally, the core efficiency is improved due to reduced cooling airflow requirements. The model is then coupled to an aircraft performance model and a typical mission is carried out. The results are compared against those of a similar configuration employing a conventional core and identical design point performance. For the given aircraft-mission combination and assuming a 10% engine weight saving when using the CRC arrangement over the conventional one, a total fuel burn reduction of 1.1% is predicted.

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Advanced User-Friendly Gas Turbine Performance Calculations on a Personal Computer

Cited by 51 publications

References 0 publications

Performance Analysis of a 50KW Turbogenerator Gas Turbine Engine

Performance Analysis of a 50KW Turbogenerator Gas Turbine Engine

A Mobile Test Rig for Micro Gas Turbines Based on a Thermal Power Measurement Approach

Modeling Contra-Rotating Turbomachinery Components for Engine Performance Simulations: The Geared Turbofan With Contra-Rotating Core Case

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