Direct Integration of Axial Turbomachinery Preliminary Aerodynamic Design Calculations in Engine Performance Component Models

2018 ◽  
Author(s):  
Ioannis Kolias ◽  
Alexios Alexiou ◽  
Nikolaos Aretakis ◽  
Konstantinos Mathioudakis
Keyword(s):  
Axial Flow ◽  
Engine Performance ◽  
Single Step ◽  
Design Calculation ◽  
Aerodynamic Design ◽  
Performance Modelling ◽  
Engine Design ◽  
And Performance ◽  
Design Calculations ◽  
Component Models

In the context of an engine design calculation, isentropic or polytropic efficiencies of turbomachinery components are assumed at the outset of the cycle analysis and their values are updated or validated following the aerodynamic design of the components. In the present paper, aerodynamic design calculations of axial-flow compressors and turbines are directly integrated into the corresponding performance component models. This creates a consistent, single-step preliminary design and performance modelling process using a relatively small number of physical and geometric inputs. The aerodynamic design for establishing a component’s overall efficiency is accomplished through a mean-line, stage-by-stage approach where the stagewise isentropic efficiency is calculated employing either loss or semi-empirical correlations. From this process, the stagewise flow annulus radii are also obtained and are used to axially size the component stages assuming the blade aspect ratio and axial gapping distributions. The component flowpath geometry is then produced by simply “stacking” axially the component stages. The developed method is validated against publicly available data for a high-pressure compressor and a low-pressure turbine. Finally, the effectiveness of the method is demonstrated by considering the multi-point design of a High Bypass Ratio Geared Turbofan Engine with bypass Variable Area Nozzle.

scholarly journals CFD Study of Nozzle Configurations for Ultra High Bypass Engines

1993 ◽  
Author(s):  
H. Zimmermann ◽  
R. Gumucio ◽  
K. Katheder ◽  
A. Jula
Keyword(s):  
Engine Performance ◽  
Operating Conditions ◽  
Aerodynamic Design ◽  
Thrust Coefficient ◽  
Optimum Range ◽  
Installation Effects ◽  
Wide Range ◽  
And Performance ◽  
Aircraft Aerodynamics ◽  
Bypass Ratio

Performance and aerodynamic aspects of ultra-high bypass ratio ducted engines have been investigated with an emphasis on nozzle aerodynamics. The interference with aircraft aerodynamics could not be covered. Numerical methods were used for aerodynamic investigations of geometrically different aft end configurations for bypass ratios between 12 and 18, this is the optimum range for long missions which will be important for future civil engine applications. Results are presented for a wide range of operating conditions and effects on engine performance are discussed. The limitations for higher bypass ratios than 12 to 18 do not come from nozzle aerodynamics but from installation effects. It is shown that using CFD and performance calculations an improved aerodynamic design can be achieved. Based on existing correlations, for thrust and mass-flow, or using aerodynamic tailoring by CFD and including performance investigations, it is possible to increase the thrust coefficient up to 1%.

Aerodynamic Design and Performance of Five-Stage Transonic Axial-Flow Compressor

1961 ◽  
Vol 83 (3) ◽  
pp. 303-320 ◽  
Author(s):  
Karl Kovach ◽  
D. M. Sandercock
Keyword(s):  
Research Work ◽  
Axial Flow ◽  
Performance Characteristics ◽  
Research Center ◽  
Aerodynamic Design ◽  
Axial Flow Compressor ◽  
Turbojet Engine ◽  
And Performance ◽  
Flow Compressor ◽  
Work Done

A five-stage axial-flow compressor with all rotors operating with transonic relative inlet Mach numbers was designed as a research vehicle at the Lewis Research Center in 1952. The compressor was designed and tested as a component of a turbojet engine. This paper summarizes the research work done on this compressor including the aerodynamic design and detailed performance characteristics.

Computational Analysis in Test Cell Design With Application in Emissions Control

2014 ◽  
Author(s):  
Paul Lee ◽  
Ligong Yang ◽  
Caner Demirdogen
Keyword(s):  
Performance Test ◽  
Combustion Engine ◽  
Engine Performance ◽  
Test Cell ◽  
Cell Design ◽  
Engine Design ◽  
Computational Fluid Dynamics Cfd ◽  
Test Cells ◽  
And Performance ◽  
Conversion Efficiencies

Computer-Aided Engineering (CAE) tools have been widely used in the design of automotive components and systems. Methods, procedures and measurables for analyses involving Internal Combustion Engine (ICE) components are well-defined and well developed. Comparatively, significantly less attention has been paid to the design and analysis of test cells. Better designed test cells will lead to increased test cell availability and thus also increases engine performance test opportunities. This trend was observed in Cummins Inc. where CAE-guided test cell designs improved test-cell availability and rate of engine development. Here, improved conversion efficiencies in test cell Selective Catalyst Reduction (SCR) modules were predicted using Computational Fluid Dynamics (CFD) tools, and validated against data collected from the test cells. The resultant improvements resulted in dramatic increases in test cell up-time. This paper documents how CAE tools commonly used in engine design were successfully expanded to aid the design of Cummins Inc. test cells. It presents the CFD methods that were used in this analysis, compares CFD predictions to actual conversion efficiencies in the SCR module, and also proposes a set of analysis tasks and methods that can be applied to improve test cell design and performance in the future.

Modelling and Assessment of Compressor Faults on Marine Gas Turbines

2012 ◽  
Author(s):  
I. Roumeliotis ◽  
N. Aretakis ◽  
K. Mathioudakis ◽  
E. A. Yfantis
Keyword(s):  
Gas Turbines ◽  
Engine Performance ◽  
Performance Model ◽  
Operating Conditions ◽  
Pollutant Emissions ◽  
Maximum Speed ◽  
Performance Modelling ◽  
Engine Operation ◽  
Marine Propulsion ◽  
And Performance

Any prime mover exhibits the effects of wear and tear over time, especially when operating in a hostile environment. Marine gas turbines operation in the hostile marine environment results in the degradation of their performance characteristics. A method for predicting the effects of common compressor degradation mechanisms on the engine operation and performance by exploiting the “zooming” feature of current performance modelling techniques is presented. Specifically a 0D engine performance model is coupled with a higher fidelity compressor model which is based on the “stage stacking” method. In this way the compressor faults can be simulated in a physical meaningful way and the overall engine performance and off design operation of a faulty engine can be predicted. The method is applied to the case of a twin shaft engine, a configuration that is commonly used for marine propulsion. In the case of marine propulsion the operating profile includes a large portion of off-design operation, thus in order to assess the engine’s faults effects, the engine operation should be examined with respect to the marine vessel’s operation. For this reason, the engine performance model is coupled to a marine vessel’s mission model that evaluates the prime mover’s operating conditions. In this way the effect of a faulty engine on vessels’ mission parameters like overall fuel consumption, maximum speed, pollutant emissions and mission duration can be quantified.

Numerical Simulation of Valve Timing and Size on a Compressed Air Engine Performance

2011 ◽  
Vol 130-134 ◽  
pp. 781-785
Author(s):  
Ye Jian Qian ◽  
Cheng Ji Zuo ◽  
Zhi Fang Chen ◽  
Hong Ming Xu ◽  
Miroslaw L. Wyszynski
Keyword(s):  
Numerical Simulation ◽  
Renewable Energy ◽  
Engine Performance ◽  
Compressed Air ◽  
System Model ◽  
Valve Timing ◽  
Engine Design ◽  
Engine System ◽  
Critical Requirement ◽  
And Performance

The compressed air engine is receiving increasingly worldwide attention because it takes advantage of renewable energy and has zero exhaust emissions. This paper presents a systematic study on valve timing and size of a prototype compressed air engine for optimizing its efficiency and performance. An in-house air engine system model has been developed using the FLOWMASTER platform. The simulated results show that the optimizing valve timings is probably the most critical requirement in the compressed air engine design process.

New Approach of Whole Engine Structural System Design

2014 ◽  
Author(s):  
Masaharu Andoh ◽  
Tatsuhito Honda ◽  
Kikuo Takamatsu
Keyword(s):  
Engine Performance ◽  
Design Approach ◽  
Jet Engines ◽  
Structural System ◽  
New Approach ◽  
Jet Engine ◽  
Conventional Design ◽  
Engine Design ◽  
Current Design ◽  
And Performance

Fuel-efficient jet engines are developed by many companies. In the conventional design approach of a jet engine, many parameters are investigated independently. Consequently, a developed jet engine by this approach meets conventional design criteria but there is still room for improvement of engine performance. In this research, the new design approach of a jet engine that integrates these design objectives is developed and performance of a jet engine is evaluated. The goal is to develop the design approach of a fuel-efficient and robust jet engine. In current design, a jet engine is developed with a focus on not only performance improvement but also robustness. Therefore, Taguchi method is adopted in order to assess robustness. By this method, a jet engine is optimized based on the analysis that minimizes deterioration and variation of SFC. As a result, more efficient engine design is realized with the new design approach that directly deals with SFC.

Risk Monitoring During Design and Development of Aircraft Engines Using Monte Carlo Simulations and Performance Model

2009 ◽  
Author(s):  
Hassan Abdullahi ◽  
Klaus-Juergen Schmidt
Keyword(s):  
Monte Carlo ◽  
Monte Carlo Simulations ◽  
New Technologies ◽  
Engine Performance ◽  
Performance Model ◽  
Design And Development ◽  
Risk Monitoring ◽  
Engine Design ◽  
And Performance ◽  
Time Frames

The process of engine design and development is very complex since it comprises various disciplines with their own sub-processes. In addition, the requirements the new generation of engines has to meet become more and more ambitious, which calls for the employment of new technologies. But this involves a very high risk with regard to fulfilling specification requirements, and also with regard to adherence to budgets as well as time frames. In this paper, an approach of risk monitoring during the engine design and development phase is presented. The approach uses Monte-Carlo simulations, which are based on an engine performance synthesis model. For the purpose, a helicopter engine is used as an example for demonstration of the method.

Design and Performance of a Controlled Turbocharging System on Marine Diesel Engines

2006 ◽  
Author(s):  
Ioannis Vlaskos ◽  
Ennio Codan ◽  
Nikolaos Alexandrakis ◽  
George Papalambrou ◽  
Marios Ioannou ◽  
...  
Keyword(s):  
Steady State ◽  
Engine Performance ◽  
Operating Conditions ◽  
Electric Actuator ◽  
Engine Simulation ◽  
Engine Control System ◽  
Turbocharging System ◽  
Compressor Impeller ◽  
Marine Diesel ◽  
And Performance

The paper describes the design process for a controlled pulse turbocharging system (CPT) on a 5 cylinder 4-stroke marine engine and highlights the potential for improved engine performance as well as reduced smoke emissions under steady state and transient operating conditions, as offered by the following technologies: • controlled pulse turbocharging, • high pressure air injection onto the compressor impeller as well as into the air receiver, and • an electronic engine control system, including a hydraulic powered electric actuator. Calibrated engine simulation computer models based on the results of tests performed on the engine in its baseline configuration were used to design the CPT components. Various engine tests with CPT under steady state and transient operating conditions show the engine optimization process and how the above-mentioned technologies benefit engine behavior in both generator and propeller law operation.

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