A new compilation method of general standard test load spectrum for aircraft engine
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Qi Lu
,
Cong Xu
Abstract
Based on the existing compilation technology of load spectrum, this paper proposed a new method for the compilation of the general standard test load spectrum of aircraft engine. On the premise of meeting operating requirements of the actual condition and the basic life test, it simplifies the test load conditions and overcomes the shortage of the existing technology. According to the actual flight of aircraft engine, the load spectrum of a flight mission profile was divided into three parts: the take-off phase, the middle-flight phase, and the landing phase. The proposed compilation method ensures that the generated load spectrum of the take-off phase and landing phase is consistent with the actual flight, and the load spectrum of the middle-flight phase is programmed according to a certain method so that a simple load cycle sequence can be implemented. On that basis, the load spectrum was analyzed and compiled by subsection. The general standard test load spectrum lays the foundation for carrying out the life test and reduces the error between the test and practical use. Since the parameters of the engine load are standardized in the process of compiling, the method can be widely used in various types of engines.
Funding source: National Basic Research Program of China
Funding source: National Natural Science Foundation of China
Award Identifier / Grant number: 51675266
Funding source: Fundamental Research Funds for the Central Universities
Award Identifier / Grant number: NJ20160038
Award Identifier / Grant number: NS2017011
Funding source: Foundation of Graduate Innovation Center in NUAA
Award Identifier / Grant number: kfjj20170220
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This study was financially supported by the National Science and Technology Major Project (J2019-V-0009-0103, J2019-IV-0017-0085. DOI: http://dx.doi.org/10.13039/501100018537), Jiangsu Province Key Laboratory of Aerospace Power System (CEPE2020004).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Robust Fault Identification of Turbofan Engines Sensors Based on Fractional-Order Integral Sliding Mode Observer
- A new compilation method of general standard test load spectrum for aircraft engine
- Numerical Investigation on the Effects of Vortex Generator Locations on Film Cooling Performance
- The Effect of the Circumferential Position of Duct Hole on the Non-uniformity in the Axial Compressor
- Surplus Power Approach to Diagnose Gas Turbine Engine Starting Characteristics
- A Flow Dynamic Characteristic Analysis of A Single Radial Swirler Combustor
- Investigation on the Jet Stiffness Characteristics of a Novel Plasma Igniter
- Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor
- Multidisciplinary Design Optimization of the Composite Cooling Structure for Nickel-based Alloy Turbine Blade
- Experimental Study of Non-Premixed Flames of Liquefied Petroleum Gas and Air in Cross-Flow and the Effects of Fuel Properties on Flame Stability
Articles in the same Issue
- Frontmatter
- Original Research Articles
- Robust Fault Identification of Turbofan Engines Sensors Based on Fractional-Order Integral Sliding Mode Observer
- A new compilation method of general standard test load spectrum for aircraft engine
- Numerical Investigation on the Effects of Vortex Generator Locations on Film Cooling Performance
- The Effect of the Circumferential Position of Duct Hole on the Non-uniformity in the Axial Compressor
- Surplus Power Approach to Diagnose Gas Turbine Engine Starting Characteristics
- A Flow Dynamic Characteristic Analysis of A Single Radial Swirler Combustor
- Investigation on the Jet Stiffness Characteristics of a Novel Plasma Igniter
- Investigations of Combustor Inlet Swirl on the Liner Wall Temperature in an Aero Engine Combustor
- Multidisciplinary Design Optimization of the Composite Cooling Structure for Nickel-based Alloy Turbine Blade
- Experimental Study of Non-Premixed Flames of Liquefied Petroleum Gas and Air in Cross-Flow and the Effects of Fuel Properties on Flame Stability
