scholarly journals Scale effects on conventional and intercooled turbofan engine performance-CORRIGENDUM

2017 ◽  
Vol 121 (1242) ◽  
pp. 1186-1186
Author(s):  
A. Rolt ◽  
V. Sethi ◽  
F. Jacob ◽  
J. Sebastiampillai ◽  
C. Xisto ◽  
...  
Keyword(s):  
Scale Effects ◽  
Engine Performance ◽  
Turbofan Engine ◽  
Correct Equation ◽  
Image Position

In the article by Rolt(1), there was an error in Equation (2). The correct equation is republished here. 2$$\begin{equation} {W_c} = \ \frac{{{W_{\it cref}}\left( {{T_{\it grel}} - {T_{\it cref}}} \right){{({W_4}/{W_{\it 4ref}})}^{0.65}}}}{{\left( {{T_{\it gref}} - {T_c}} \right)}}\ \ \ \ \ \ \ \end{equation}$$

Analysis of Effect of Advanced Technique Configurations on Overall Performance of High Bypass Turbofan Engine

2014 ◽  
Author(s):  
Liu Jian Jun
Keyword(s):  
Air Flow ◽  
Engine Performance ◽  
Performance Model ◽  
Direct Drive ◽  
Nozzle Throat ◽  
Advanced Technique ◽  
Turbofan Engine ◽  
Overall Performance ◽  
Cooling Air Flow ◽  
Cooling Air

An analytical study was undertaken using the performance model of a two spool direct drive high BPR 300kN thrust turbofan engine, to investigate the effects of advanced configurations on overall engine performance. These include variable bypass nozzle, variable cooling air flow and more electric technique. For variable bypass nozzle, analysis on performance of outer fan at different conditions indicates that different operating points cannot meet optimal performance at the same time if the bypass nozzle area kept a constant. By changing bypass nozzle throat area at different states, outer fan operating point moves to the location where airflow and efficiency are more appropriate, and have enough margin away from surge line. As a result, the range of variable area of bypass nozzle throat is determined which ensures engine having a low SFC and adequate stability. For variable cooling airflow, configuration of turbine cooling air flow extraction and methodology for obtaining change of cooling airflow are investigated. Then, base on temperature analysis of turbine vane and blade and resistance of cooling airflow, reduction of cooling airflow is determined. Finally, using performance model which considering effect of cooling air flow on work and efficiency of turbine, variable cooling airflow effect on overall performance is analyzed. For more electric technique, the main characteristic is to use power off-take instead of overboard air extraction. Power off-take and air extraction effect on overall performance of high bypass turbofan engine is compared. Investigation demonstrates that power offtake will have less SFC.

Entropy, Energy and Exergy for Measuring PW4000 Turbofan Sustainability

2019 ◽  
Vol 0 (0) ◽  
Author(s):  
Hakan Aygun ◽  
Onder Turan
Keyword(s):  
Thrust Force ◽  
Engine Performance ◽  
Sustainable Growth ◽  
Performance Parameters ◽  
Turbofan Engine ◽  
Effect Factor ◽  
Energy And Exergy ◽  
And Performance ◽  
Engine Components ◽  
Main Engine

Abstract This study focuses on for a PW4000 high-bypass turbofan engine using energy, exergo-sustainable and performance viewpoint. For this aim, irreversibility and performance analyses are firstly performed for five main engine components at ≈260 kN maximum take-off thrust force. Besides, overall efficiency of the turbofan is determined to be 33 %, while propulsive and thermal efficiency of the turbofan are 72 % and 46 % respectively at 0.8 M and 288.15 K flight conditions. Secondly, calculation component-based exergetic assessment is carried out using exergetic indicators. According to the calculation, the exergetic efficiency of the engine is 32 %, while its waste exergy ratio is 0.678. Furthermore, exergetic sustainability measure is obtained as 0.473, while enviromental effect factor is 2.112. These indicators are also anticipated to help comprehend the connection between engine performance parameters and worldwide dimensions such as environmental effect and sustainable growth.

Thrust Reverser for a Separate Exhaust High Bypass Ratio Turbofan Engine and its Effect on Aircraft and Engine Performance

2011 ◽  
Author(s):  
Tashfeen Mahmood ◽  
Anthony Jackson ◽  
Vishal Sethi ◽  
Pericles Pilidis
Keyword(s):  
Engine Performance ◽  
Aircraft Engine ◽  
Performance Characteristics ◽  
System Level ◽  
Performance Models ◽  
Turbofan Engine ◽  
Engine Model ◽  
Rate Deceleration ◽  
Thrust Reverser ◽  
Bypass Ratio

This paper discusses thrust reversing techniques for a separate exhaust high bypass ratio turbofan engine and its effect on aircraft and engine performance. Cranfield University is developing suitable thrust reverser performance models. These thrust reverser performance models will subsequently be integrated within the TERA (Techno-economic Environmental Risk Analysis) architecture thereby allowing for more detailed and accurate representations of aircraft and engine performance during the landing phase of a typical civil aircraft mission. The turbofan engine chosen for this study was CUTS_TF (Cranfield University Twin Spool Turbofan) which is similar to the CFM56-5B4 engine and the information available in the public domain is used for the engine performance analysis along with the Gas Turbine Performance Software, ‘GasTurb 10’ [1]. The CUTEA (Cranfield University Twin Engine Aircraft) which is similar to the Airbus A320 is used alongside with the engine model for the thrust reverser performance calculations. The aim of this research paper is to investigate the effects on aircraft and engine performance characteristics due to the pivoting door type thrust reverser deployment. The paper will look into the overall engine performance characteristics and how the engine components get affected when the thrust reversers come into operation. This includes the changes into the operating point of fan, booster, HP compressor, HP turbine, LP turbine, bypass nozzle and core nozzle. Also, thrust reverser performance analyses were performed (at aircraft/engine system level) by varying the reverser exit area by ± 5% and its effect on aircraft deceleration rate, deceleration time and landing distances were observed.

An Introduction to the JT15D Engine

1969 ◽  
Author(s):  
C. B. Wrong
Keyword(s):  
High Reliability ◽  
Engine Performance ◽  
Development Programme ◽  
Market Potential ◽  
Growth Potential ◽  
Good Growth ◽  
Turbofan Engine ◽  
Component Testing ◽  
Initial Cost ◽  
Minimum Number

An analysis of the market potential for a small turbofan engine intended for business aircraft has led to the design of the JT15D. The main design objectives were low initial cost, low fuel consumption, high reliability, low maintenance costs, ease of installation and operation, and good growth potential. These objectives have been achieved using a minimum number of components and providing a simple layout. Mounting of the engine is highly flexible, and operation is straightforward. Extensive component testing has been carried out. Guaranteed engine performance was achieved early in the development programme.

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