Research Overview of Full Aero-Engine Dynamic Response Caused by Blade-Off

2013 ◽  
Vol 423-426 ◽  
pp. 1552-1557
Author(s):  
Dong Ye ◽  
Hai Jun Xuan ◽  
Lu Lu Liu
Keyword(s):  
Dynamic Response ◽  
Aviation Industry ◽  
Structure Response ◽  
Performance Requirements ◽  
Engine Vibration ◽  
Aero Engine ◽  
Engine Dynamic ◽  
Aero Engines ◽  
Rotor Dynamic ◽  
Couple Vibration

With the development of aviation industry, more and more performance requirements are submitted to aero-engines, and structure response and safety problem of aero-engine is concerned. Overview is made of the recently years full engine vibration response due to blade-off. And summary about case containment and rotor dynamic response caused by sudden unbalance in blade-off situation is presented. Then the analysis technologies and modeling methodologies of full engine blade-off structure response are focused. According to the trend, the field of couple vibration analysis should be paid more attention to in the research of full engine dynamic response during blade-off.

Modelling of Misaligned Rotor System in Aero-Engines and Interval Method Investigation

2013 ◽  
Author(s):  
Guihua Wang ◽  
Yanhong Ma ◽  
Tianrang Li ◽  
Jun Li ◽  
Jie Hong
Keyword(s):  
Dynamic Response ◽  
Rotor System ◽  
Mechanical Parameters ◽  
Lagrange Method ◽  
Interval Method ◽  
Aero Engine ◽  
Mechanical Factors ◽  
Aero Engines ◽  
Rotor Model ◽  
Engine Rotor

Based on the structural and dynamic characteristics of aero-engine rotor system, we used Lagrange method to develop a two-bearing and a multi-bearing rotor model with misalignment. An equation of motion was derived with features of response examined. Due to the uncertainty of mechanical parameters, interval method was adopted to investigate the dynamic response of rotor system with misalignment. Dynamic response and influence of the key mechanical parameters will be obtained in further research. The two times harmonic was found as a distinctive feature of misalignment and the magnitude of it in spectrum is closely related to some key mechanical factors. We also found interval method outstandingly performed in investigating dynamic response when some key parameters are uncertain.

Advanced Aero-Engines Technology Enablers: An Overview of the European Project E-BREAK

2016 ◽  
Author(s):  
Manuel Silva ◽  
Nicolas Tantot ◽  
Serge Selezneff ◽  
Mike Walsh ◽  
Rose Nyatando ◽  
...  
Keyword(s):  
Global Market ◽  
Air Travel ◽  
Air Traffic ◽  
Pollutant Emissions ◽  
Aviation Industry ◽  
Component Level ◽  
Average Growth ◽  
Enabling Technologies ◽  
Aero Engine ◽  
Aero Engines

This paper describes research carried out in the European Commission co-funded project E-BREAK (Engine BREAK through components and subsystems) focused on development of generic enabling technologies for new aero-engines. A global market forecast (2015–2034) from Airbus [1], depicts an average growth rate of 4.6% per year. Air traffic is forecasted to double in the next 15 years. It is expected, to triple in the next 20 years, according to the speech given by RRUK CEO during the Aerodays 2015 in London [2]. This high level of growth in demand for air travel represents huge opportunities as well as significant challenges for the aerospace industry. Research and Technology through collaborative European projects addresses the environmental penalties of air traffic. Europe’s aviation industry therefore faces a huge challenge to satisfy the demand whilst guaranteeing competitiveness, safety and more environmentally friendly air travel. Innovative engine configurations consequently need to be investigated in order to reduce significantly the pollutant emissions (15 to 20% for fuel consumption and CO2 and 80% reduction for NOx). Such reductions can only be achieved by considering innovative components that could be integrated and optimized in new engine configurations. In response to the above demands, aero-engine manufacturers are constantly aiming to improve gas turbine efficiency for two main reasons: to reduce environmental impact and to minimize operating costs. The E-BREAK project is aimed at the development of generic enabling technologies needed to address the challenges for future engines with higher overall pressure ratios (OPR) and bypass ratio (BPR). These technologies are developed at subsystem and component level and validated in test rigs which are equivalent to Technical Readiness Level (TRL) 5. The utility of the developed technologies are assessed using four standard study powerplants. These are turboshaft, regional turbofan, mid-size open rotor, and large turbofan, covering most of the expected future commercial aero-engine market. This article describes the technical approach followed in E-BREAK for the various technologies being investigated, these are: • Advanced sealing to reduce oil and air leakages • Variability control to ensure stability of thermodynamic cycle • High temperature resistant material and abradables to prevent fast degradation at high temperatures • Light material to prevent significant mass increase • Health monitoring system to anticipate sub-systems degradation The envisaged outcomes from E-BREAK are enablers to other EU-funded research projects focused on module maturation progress, such as LEMCOTEC dealing with high OPR modules and ENOVAL dealing with high BPR LP components.

Detection method of combustion oscillation characteristics under strong noise background

2020 ◽  
Vol 21 (6) ◽  
pp. 612
Author(s):  
Yunkun Wei ◽  
Tianhong Zhang ◽  
Zhonglin Lin ◽  
Qi Xie ◽  
Yan Zhang
Keyword(s):  
Radiation Thermometry ◽  
Hydroxyl Group ◽  
Interference Signal ◽  
Engine Vibration ◽  
Combustion Technology ◽  
Lean Fuel ◽  
Combustion Oscillation ◽  
Aero Engines ◽  
Temperature Measurement System ◽  
Multispectral Radiation Thermometry

After the lean fuel premixed combustion technology is applied to aero engines, severe combustion oscillations will be cased and led to hidden safety hazards such as engine vibration, further energy waste and other problems. Therefore, it is increasingly important to actively control combustion oscillations. In this paper, a multispectral radiation thermometry (MRT) is used to analyze the hydroxyl group, which is a measurable research object in the combustion chamber of an aero engine, and to fit the functional relationship between the radiation intensity ratio and the temperature in different bands. The theoretical value of the error is <2%. At the same time, in order to solve the problem of weak detection signal and excessive interference signal, an improved frequency domain filtering method based on fast Fourier transform is designed. Besides, the FPGA platform is used to ensure the real-time performance of the temperature measurement system, and simulations and experiments are performed. An oscillating signal with an oscillation frequency of 315 Hz is obtained on the established test platform, and the error is only 1.42%.

Aero-engine dynamic model based on an improved compact propulsion system dynamic model

2021 ◽  
pp. 095965182098408
Author(s):  
Qiangang Zheng ◽  
Yong Wang ◽  
Chongwen Jin ◽  
Haibo Zhang
Keyword(s):  
Dynamic Model ◽  
Propulsion System ◽  
System Dynamic ◽  
Inlet Temperature ◽  
System Dynamic Model ◽  
Component Level ◽  
Engine Model ◽  
Surge Margin ◽  
Aero Engine ◽  
Engine Dynamic

The modern advanced aero-engine control methods are onboard dynamic model–based algorithms. In this article, a novel aero-engine dynamic modeling method based on improved compact propulsion system dynamic model is proposed. The aero-engine model is divided into inlet, core engine, surge margin and nozzle models for establishing sub-model in the compact propulsion system dynamic model. The model of core engine is state variable model. The models of inlet, surge margin and nozzle are nonlinear models which are similar to the component level model. A new scheduling scheme for basepoint control vector, basepoint state vector and basepoint output vector which considers the change of engine total inlet temperature is proposed to improve engine model accuracy especially the steady. The online feedback correction of measurable parameters is adopted to improve the steady and dynamic accuracy of model. The modeling errors of improved compact propulsion system dynamic model remain unchanged when engine total inlet temperature of different conditions are the same or changes small. The model accuracy of compact propulsion system dynamic model, especially the measurable parameters, is improved by online feedback correction. Moreover, the real-time performance of compact propulsion system dynamic model and improved compact propulsion system dynamic model are much better than component level model.

scholarly journals Aero-Engine Fault Diagnosis Using Improved Local Discriminant Bases and Support Vector Machine

2014 ◽  
Vol 2014 ◽  
pp. 1-9 ◽  
Author(s):  
Jianwei Cui ◽  
Mengxiao Shan ◽  
Ruqiang Yan ◽  
Yahui Wu
Keyword(s):  
Support Vector Machine ◽  
Fault Diagnosis ◽  
Wavelet Packet ◽  
Energy Difference ◽  
Test System ◽  
Support Vector ◽  
Svm Classifier ◽  
Aero Engine ◽  
Aero Engines ◽  
Optimal Set

This paper presents an effective approach for aero-engine fault diagnosis with focus on rub-impact, through combination of improved local discriminant bases (LDB) with support vector machine (SVM). The improved LDB algorithm, using both the normalized energy difference and the relative entropy as quantification measures, is applied to choose the optimal set of orthogonal subspaces for wavelet packet transform- (WPT-) based signal decomposition. Then two optimal sets of orthogonal subspaces have been obtained and the energy features extracted from those subspaces appearing in both sets will be selected as input to a SVM classifier to diagnose aero-engine faults. Experiment studies conducted on an aero-engine rub-impact test system have verified the effectiveness of the proposed approach for classifying working conditions of aero-engines.

Low Order Modeling for Fan and Outlet Guide Vanes in Aero-Engines

2019 ◽  
Vol 141 (3) ◽  
Author(s):  
Jiahuan Cui ◽  
Rob Watson ◽  
Yunfei Ma ◽  
Paul Tucker
Keyword(s):  
Detailed Analysis ◽  
Immersed Boundary Method ◽  
Low Cost ◽  
Immersed Boundary ◽  
Test Case ◽  
Guide Vanes ◽  
Compression System ◽  
Aero Engine ◽  
Aero Engines ◽  
Low Order

Intakes of reduced length have been proposed with the aim of producing aero-engines with higher efficiency and reduced weight. As the intake length decreases, it is expected that stronger effects of the fan on the flow over the intake lip will be seen. If the effects of the fan cannot be ignored, a low-cost but still accurate fan model is of great importance for designing a short-intake. In this paper, a low order rotor/stator model, the immersed boundary method with smeared geometry (IBMSG), has been further developed and validated on a rig test case. The improved IBMSG is more robust than the original. The rig test case used for validation features a low-pressure compression system with a nonaxisymmetric inflow, which is representative of the inlet condition of an aero-engine at its cruise condition. Both the fan and the outlet guide vanes (OGVs) are modeled using IBMSG. A detailed analysis is carried out on the flow both upstream and downstream of the fan. After validating the IBMSG method against the rig test case, a short-intake case, coupled with a fan designed for the next generation of aero-engines, is further investigated. It is found that compared with the intake-alone case, the inflow distortion at the fan face is significantly reduced by the presence of fan. Due to this increased interaction between the fan and the flow over the intake lip, accounting for the effects of the downstream fan is shown to be essential when designing a short intake.

Modern Methods of Testing Aero-Engines and Power Plants

1950 ◽  
Vol 54 (474) ◽  
pp. 327-358 ◽  
Author(s):  
A. C. Lovesey
Keyword(s):  
Power Plants ◽  
Test Equipment ◽  
Flow Meter ◽  
Fuel Flow ◽  
Modern Methods ◽  
Aero Engine ◽  
Aero Engines

In the early days of aero-engines the test equipment was limited to little more than a brake or dynamometer, a fuel flow meter and a few thermometers, and the development of these engines in the direction of better performance and reliability, to a large extent, was an art, built up of experience aided by instinct, of deducing the happenings inside an engine from the few meagre measurements obtainable.Nevertheless, the aero-engine made healthy progress, became more complicated in the process, and introduced many more problems.

scholarly journals A mimicking technique of back pressure in the hardware-in-the-loop simulation of a fuel control unit

SIMULATION ◽  
2019 ◽  
Vol 96 (4) ◽  
pp. 375-385 ◽  
Author(s):  
Yuan Yuan ◽  
Zhiwen Zhao ◽  
Tianhong Zhang
Keyword(s):  
Control Unit ◽  
Back Pressure ◽  
Hardware In The Loop ◽  
Fuel System ◽  
Working Process ◽  
Aero Engine ◽  
Aero Engines ◽  
Performance Results ◽  
The Impact ◽  
Hil Simulation

In the hardware-in-the-loop (HIL) simulation of the fuel control unit (FCU) for aero-engines, the back pressure has a great impact on the metered fuel, thus influencing the confidence of the simulation. During the practical working process of an aero-engine, the back pressure of the FCU is influenced by the combined effect of the pressure of the combustion chamber, the resistance of the spray nozzles, and the resistance of the distribution valve. There is a need to study the the mimicking technique of FCU back pressure. This paper models the fuel system of an aero-engine so as to reveal the impact of FCU back pressure on the metered fuel and come up with a scheme to calculate the equivalent FCU back pressure. After analyzing the requirements for mimicking the pressure, an automatic regulating facility is designed to adjust the FCU back pressure in real time. Finally, experiments are carried out to verify its performance. Results show that the mimicking technique of back pressure is well suited for application in HIL simulation. It is able to increase the confidence of the simulation and provide guidance to the implementation of mimicking the FCU back pressure.

Preliminary Research on Future Smart Engine Architecture

2020 ◽  
Author(s):  
Yudong Liu ◽  
Min Chen ◽  
Hailong Tang
Keyword(s):  
Aerospace Industry ◽  
Research Projects ◽  
Engine Design ◽  
Engine Component ◽  
Aero Engine ◽  
The Future ◽  
Component Matching ◽  
Matching Mechanism ◽  
Preliminary Research ◽  
Aero Engines

Abstract Aero engines that fit the future have now increasingly attracted the attention of aerospace industry and academia. With this trend, many research projects have been carried out to explore future aero engine technologies. This paper focuses on engine design field, and aims to satisfy the future flight missions that may be unpredictably varying. However, the intrinsic strong coupling of engine component matching mechanism blocks acceleration of engine design. Under this condition, this paper comes up with the concept of smart engine architecture that via a series of engine decoupling strategies, the components can be decoupled to an extent that by properly selecting and assembling them, an engine that satisfies certain flight mission can be designed, this is named mission-oriented pluggable design mode in this paper. Following this idea, a multi-purpose engine design scheme is presented to demonstrate the potential of this engine design mode, and further value of smart engine architecture is discussed.

Sign in / Sign up

Export Citation Format

Share Document