Research of the XF3-1 Turbofan Engine

1978 ◽  
Author(s):  
M. Kohzu ◽  
H. Chinone ◽  
M. Miyake ◽  
K. Murashima ◽  
K. Yamanaka ◽  
...  
Keyword(s):  
Research Program ◽  
Engine Performance ◽  
Bench Test ◽  
Turbofan Engine ◽  
The Status ◽  
Test Engine ◽  
Matching Performance ◽  
Basic Studies ◽  
Front Fan ◽  
Bypass Ratio

A research program of low bypass ratio small front fan engines has been in process at Third Research Center of Technical Research and Development Institute of Japan Defence Agency since 1975. The final target of this program is the development of the propulsion engine for the high subsonic small aircraft. As the first phase of this program, the bench test engine XF3-1 was manufactured and the basic studies of the overall engine matching performance and the effect of each component on the engine performance have been carried out. This paper describes the XF3-1 engine, reviews the status of the research and presents the major engineering progress attained through the research.

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.

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

2012 ◽  
Author(s):  
Tashfeen Mahmood ◽  
Anthony Jackson ◽  
Syed H. Rizvi ◽  
Pericles Pilidis ◽  
Mark Savill ◽  
...  
Keyword(s):  
Engine Performance ◽  
Engine Exhaust ◽  
Turbofan Engine ◽  
The Public ◽  
Engine Model ◽  
Turbine Performance ◽  
Lp Turbine ◽  
Engine Components ◽  
Thrust Reverser ◽  
Bypass Ratio

This paper discusses thrust reverser techniques for a mixed exhaust high bypass ratio turbofan engine and its effect on aircraft and engine performance. The turbofan engine chosen for this study was CUTS_TF (Cranfield University Three Spool Turbofan) which is similar to Rolls-Royce TRENT 772 engine and the information available for this engine in the public domain is used for the engine performance analysis along with the Gas Turbine Performance Software, GasTurb 10. The CUTEA (Cranfield University Twin Engine Aircraft) which is similar to the Airbus A330 is used along side with the engine model for the thrust reverser performance calculations. The aim of this research paper is to investigate the effects on mixed exhaust engine performance due to the pivoting door type thrust reverser deployment. The paper looks into the engine off-design performance characteristics and how the engine components get affected when the thrust reverser come into operation. This includes the changes into the operating point of fan, IP compressor, HP compressor, HP turbine, IP turbine, LP turbine and the engine exhaust nozzle. Also, the reverser deployment effect on aircraft, deceleration time and landing distances are discussed.

Estimating the Drag Developed by a High Bypass Ratio Turbofan Engine

2018 ◽  
Author(s):  
M. S. Zawislak ◽  
D. J. Cerantola ◽  
A. M. Birk
Keyword(s):  
Engine Performance ◽  
Operating Conditions ◽  
Zone Model ◽  
Pressure System ◽  
Cross Sectional ◽  
Turbofan Engine ◽  
Engine Model ◽  
Integration Techniques ◽  
Drag Analysis ◽  
Bypass Ratio

A high bypass ratio turbofan engine capable of powering the Boeing 757 was considered for thrust and drag analysis. A quasi-2D engine model applying the fundamental thermodynamics conservation equations and practical constraints determined engine performance and provided cross-sectional areas in the low-pressure system. Coupled with suggestions on boat-tail angle and curvature from literature, a representative bypass duct and primary exhaust nozzle was created. 3D steady-RANS simulations using Fluent® 18 were performed on a 1/8th axisymmetric section of the geometry. A modified 3D fan zone model forcing radial equilibrium was used to model the fan and bypass stator. Takeoff speed and cruise operating conditions were modeled and simulated to identify changes in thrust composition and intake sensitivity. Comparison between net thrust predictions by the engine model and measured in CFD were within grid uncertainty and model sensitivity at cruise. Trends observed in a published database were satisfied and calculations coincided with GasTurb™ 8.0. Verification of thrust in this manner gave confidence to the aerodynamic performance prediction of this modest CFD. Obtaining a baseline bypass design would allow rapid testing of aftermarket components and integration techniques in a realistic flow-field without reliance on proprietary engine data.

Status Report of the Turbofan Engine Development Program in Japan

1977 ◽  
Author(s):  
M. Matsuki ◽  
T. Torisaki ◽  
K. Miyazawa ◽  
M. Itoh
Keyword(s):  
Research And Development ◽  
Development Program ◽  
Status Report ◽  
Second Phase ◽  
Turbofan Engine ◽  
Turbofan Engines ◽  
The Status ◽  
Target Performance ◽  
Bypass Ratio ◽  
Engine Development

A National Research and Development Program of high bypass ratio turbofan engines has been in process in Japan since 1971. Target performance characteristics of the first-phase 5-ton thrust class engines have been attained, and development of the second-phase engines has been started in 1976. This paper reviews the status of the program, discusses some engineering progress attained, and presents an outline of the second-phase program and engines.

scholarly journals High Bypass Ratio Compound Fan-Shaft Engines for Convertible Rotary Wing Aircraft

1969 ◽  
Author(s):  
L. l’Anson
Keyword(s):  
Pressure Ratio ◽  
Engine Performance ◽  
Power Sharing ◽  
Helicopter Rotor ◽  
Drive Power ◽  
Rotor Drive ◽  
Fan Speed ◽  
Front Fan ◽  
Rotary Wing ◽  
Bypass Ratio

This paper presents design arrangements and performances of high bypass ratio compound fan-shaft engines. Helicopter rotor drive power can be obtained from the propulsion fan engine by unloading the fan. This is accomplished by using variable fan guide vanes that can be closed to reduce fan air flow or by reducing fan speed. These methods of unloading the fan are substantiated by the results of tests. The basic designs considered are for engines in the 5 to 30 lb/sec gas producer airflow size class and which have a two-spool coaxial front fan with a bypass ratio of approximately 8.0 and pressure ratio of approximately 1.4. The front fan configuration is used to superchange the gas producer. The flow of energy that results during power sharing between propulsive fan thrust and helicopter rotor drive power is discussed; in addition, fan shaft engine performance data are presented as applied to representative stowed-rotor convertiplanes of 15,000 and 60,000-lb design gross weights.

Influence of Turbine Blade Cooling Efficiency on Turbofan Engine Performance

2013 ◽  
Vol 444-445 ◽  
pp. 1272-1276
Author(s):  
Li Ya Zhu ◽  
Qin Huang
Keyword(s):  
Turbine Blade ◽  
Large Scale ◽  
Pressure Ratio ◽  
Engine Performance ◽  
Cooling Efficiency ◽  
Turbofan Engine ◽  
Turbine Blade Cooling ◽  
Blade Cooling ◽  
Calculation Results ◽  
Bypass Ratio

On the basis of a performance emulation model of turbofan engine, a relation curve was first employed to fix the efficiency of compression components. With the turbine blade cooling efficiency being a restriction, an optimization algorithm was developed on the premise that engine cycle parameters match. The calculation results show that when the turbine blade cooling efficiency was improved at a fixed bypass ratio, the engine overall pressure ratio corresponding to the lowest specific fuel consumption (sfc) grows on a large scale, while the lowest sfc slightly drops and the specific thrust significantly boosts.

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%.

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