Study on Probability Distributions of Processing and Assembling Promoters of Aero-Engine Critical Part

2013 ◽  
Vol 290 ◽  
pp. 107-111
Author(s):  
Min Huang ◽  
Zhao Wang ◽  
Jun Yi
Keyword(s):  
Correlation Analysis ◽  
Theoretical Basis ◽  
Probability Distributions ◽  
Engine Performance ◽  
Optimal Distribution ◽  
Analysis Software ◽  
Critical Part ◽  
Aero Engine ◽  
Vibration Parameters ◽  
Engine Components

According to the characteristics of aero-engine and the study purpose of this paper, aero-engine information data were collected and screened from " Aero-engine Assembly Resume ", included: certain engine components data, assembly detection data and engine trial run data. By using the collected and screened data, correlation analysis were carried among testing parameters and among vibration parameters, correlation analysis were also carried between testing parameters or vibration parameters and components geometry parameters, assembly parameters or parameters combination which impact engine performance. From the result of correlation analysis, the key parameters strongly affecting engine performance can be found out, and then according to the value of the correlation coefficient put these parameters in queue. The optimal distribution of these parameters in queue can be determined by data analysis software, and the estimation eigenvalue of these parameter can be obtained. Purpose and significance of this paper is to improve the reliability of the components producing and assembly processing, what is more, it provides theoretical basis for the design and improvement of aero-engine.

Non-Linear Aeromechanical Behaviour of Axial Core Compressor Stator Vanes

2007 ◽  
Author(s):  
Caetano Peng
Keyword(s):  
Integrated Design ◽  
Engine Performance ◽  
Forced Response ◽  
Design Tools ◽  
Virtual Testing ◽  
Aero Engine ◽  
Stator Vane ◽  
Recent Developments ◽  
Aero Engines ◽  
Engine Components

This paper highlights some engine non-linearities that can affect both performance and robustness of aero engines. It pays particular attention to non-linearities generated at the stator vane contact end joints. These non-linearities resulting from friction contact joints affect the vane modeshapes, damping and forced response. This work proposes upper and lower bound solutions based on vane end restraints non-linearities to predict conservative forced response of stator vanes. Some non-linearities such as those caused by mistuning can be beneficial to the component and system. There are also non-linearities that can be detrimental to engine performance, robustness and reliability. Moreover, it proposes and discusses the concept of temporal HCF or CCF lifing method. Recent developments in FE, CFD, mistuning, forced response and probabilistic codes can help to create more integrated design tools that incorporate time-dependent non-linearities in the lifing of aero engine components. Computations performed here demonstrated some level of component virtual testing. These analyses are important component virtual testing that will be gradually extended to whole aero engine virtual testing.

Design and Application of a Multidisciplinary Predesign Process for Novel Engine Concepts

2018 ◽  
Vol 141 (1) ◽  
Author(s):  
Stanislaus Reitenbach ◽  
Alexander Krumme ◽  
Thomas Behrendt ◽  
Markus Schnös ◽  
Thomas Schmidt ◽  
...  
Keyword(s):  
Data Model ◽  
Structural Design ◽  
Engine Performance ◽  
Turbofan Engine ◽  
Engine Model ◽  
Modeling Techniques ◽  
Aero Engine ◽  
Open Rotor ◽  
Definition Of ◽  
Engine Components

The purpose of this paper is to present a multidisciplinary predesign process and its application to three aero-engine models. First, a twin spool mixed flow turbofan engine model is created for validation purposes. The second and third engine models investigated comprise future engine concepts: a counter rotating open rotor (CROR) and an ultrahigh bypass turbofan. The turbofan used for validation is based on publicly available reference data from manufacturing and emission certification. At first, the identified interfaces and constraints of the entire predesign process are presented. An important factor of complexity in this highly iterative procedure is the intricate data flow, as well as the extensive amount of data transferred between all involved disciplines and among different fidelity levels applied within the design phases. To cope with the inherent complexity, data modeling techniques have been applied to explicitly determine required data structures of those complex systems. The resulting data model characterizing the components of a gas turbine and their relationships in the design process is presented in detail. Based on the data model, the entire engine predesign process is presented. Starting with the definition of a flight mission scenario and resulting top level engine requirements, thermodynamic engine performance models are developed. By means of these thermodynamic models, a detailed engine component predesign is conducted. The aerodynamic and structural design of the engine components are executed using a stepwise increase in level of detail and are continuously evaluated in context of the overall engine system.

Influence of secondary flow on aero-engine performance

2013 ◽  
Author(s):  
Xiao-bo Zhang ◽  
Zhan-xue Wang ◽  
Zeng-wen Liu
Keyword(s):  
Secondary Flow ◽  
Engine Performance ◽  
Aero Engine

Investigation of the Water Guided Laser Micro-Jet Machining of Aero Engine Components

2017 ◽  
Author(s):  
Zhigang Wang
Keyword(s):  
Energy Density ◽  
Material Removal ◽  
Removal Rate ◽  
Cutting Speed ◽  
Potential Method ◽  
Laser Machining ◽  
Aero Engine ◽  
Engine Components ◽  
The Relationship ◽  
Dual Laser

The water guided laser micro-jet (LMJ) is a new potential method to machine aero engine parts with much less heat affected area and faster cutting speed than dry laser machining. The focus of this paper is to investigate the energy density and material removal for a dual-laser LMJ system. Then, the effects of dominated parameters on the energy density of LMJ are analyzed. Finally, a mathematical model is developed to describe the relationship between dominant laser parameters with the energy density of LMJ and material removal rate followed by machining case studies of aero engine components.

Vibration Spectra as a Feedback for Controlling Multicylinder Engine Performance

1992 ◽  
Vol 3 (2) ◽  
pp. 176-192
Author(s):  
T.W. Abou-Arab ◽  
M. Othman ◽  
Y.S.H. Najjar
Keyword(s):  
Engine Speed ◽  
Engine Performance ◽  
Feedback System ◽  
Operating Conditions ◽  
Flow Induced Vibration ◽  
Vibration Spectra ◽  
Parametric Studies ◽  
Vibration Pattern ◽  
Engine Components ◽  
Heat And Fluid Flow

Increasing requirements for vehicle confort, economy and reliability lead some investigators to consider the relationships between the mechanical vibrations with the heat and fluid flow induced vibration and noise in a more accurate manner. This paper describes the variation of the vibration phenomena associated with the motion of some engine components under different operating conditions. The measured vibration spectra indicates its capability in predicting symptoms of early engine failures, hence, expediting their control using a suitable feedback system. Parametric studies involving the effect of air-fuel ratio, ignition timing and engine speed on the vibration pattern are also carried out. These studies indicate that the amplitude of vibration decreases as the speed increases then increases again after certain engine speed. The effect of ignition system characteristic on the induced vibration are obtained and the correlation between the developed power and the engine dynamics over a range of operating conditions are discussed.

Improvement of Variation Propagation Control in Mechanical Assembly Using Adjustment Assembly Technique

2017 ◽  
Vol 870 ◽  
pp. 459-464 ◽  
Author(s):  
Chuan Zhi Sun ◽  
Lei Wang ◽  
Jiu Bin Tan ◽  
Bo Zhao ◽  
Guo Liang Jin ◽  
...  
Keyword(s):  
Assembly Model ◽  
Mechanical Assembly ◽  
Assembly Quality ◽  
Cumulative Error ◽  
Assembly Method ◽  
Variation Propagation ◽  
Rotationally Symmetric ◽  
Aero Engine ◽  
Assembly Technique ◽  
Engine Components

This paper aims to provide an assembly method to improve mechanical assembly quality. In order to improve the variation propagation control in rotationally symmetric cylindrical components assembly, the eccentric and tilt errors of a single rotor stage were taken into account using a connective assembly model and the eccentric deviation in a mechanical assembly was minimized by properly selecting component orientations. Compared to the minimum cumulative error, the maximum cumulative error was reduced by 71 percent, and the average cumulative error was reduced by 57 percent in the assembly of three components. This article provides an assembly method through variation propagation control in rotationally symmetric cylindrical components assembly. The method could be extended to rotationally symmetric cylindrical components assembly, for example in the assembly of aero-engine components.

scholarly journals On cold dwell facet fatigue in titanium alloy aero-engine components

2017 ◽  
Vol 97 ◽  
pp. 177-189 ◽  
Author(s):  
M.A. Cuddihy ◽  
A. Stapleton ◽  
S. Williams ◽  
F.P.E. Dunne
Keyword(s):  
Titanium Alloy ◽  
Aero Engine ◽  
Engine Components

Aero Engine Performance Evaluation During Missile Firing Test

2017 ◽  
Author(s):  
Sajath Kumar Manoharan ◽  
Kasram Santhosh ◽  
Mahesh P. Padwale ◽  
G. P. Ravishankar
Keyword(s):  
Performance Evaluation ◽  
Engine Performance ◽  
Flight Testing ◽  
Flow Disturbance ◽  
Fighter Aircraft ◽  
Firing Test ◽  
Aero Engine ◽  
Temperature Ramps ◽  
Air Intake ◽  
Model Engine

Evaluation of engine performance during armament firing in fighter aircraft is a vital qualification aspect for airframe engine integration. Ingestion of missile’s efflux into air intake results in rapid increase of engine inlet temperatures (temperature ramps) which cause flow disturbance to the compressor. Temperature distortion caused due to armament firing and its effect on compressor stability during flight testing is evaluated. Accordingly mitigation actions are recommended for stall/surge free operations. Distortion descriptors are assessed using simulation model (engine performance program) and results compared with engine distortion limits.

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