Effect of Porosity Parameters on the Strength of Gas Turbine Compressor Blades Made of Titanium Alloys

Pavlenkoz, D. V.

doi:10.1007/s11223-020-00139-0

Cited by 3 publications

(3 citation statements)

References 14 publications

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“…Thus, the total relative shear deformation of the billet was 5.77. The average size of the structural components (grains and subgrains) in the samples after five TE passes was in the range of 200 -500 nm for titanium alloys [25]. The size of the structural components in the original samples was 150 -300 µm.…”

Section: Twist Extrusionmentioning

confidence: 95%

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

Павленко¹,

Dvirnyk²,

Przysowa³

2020

Preprint

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BACKGROUND: Manufacturing costs, along with operational performance, are among the major factors determining the selection of the propulsion system for unmanned aerial vehicles (UAVs), especially for aerial targets and cruise missiles. OBJECTIVES: In this paper, the design requirements and operating parameters of small turbofan engines for single-use and reusable UAVs are analysed to introduce alternative materials and technologies for manufacturing their compressor blades, such as sintered titanium, a new generation of aluminium and an alloy based on titanium aluminides. METHODS: To assess the influence of severe plastic deformation (SPD) on the hardening efficiency of the proposed materials, the alloys in the coarse-grained and submicrocrystalline states were studied. Changes in physical and mechanical properties of materials were taken into account. The thermodynamic analysis of the compressor was performed in a finite element analysis system (ANSYS) to determine the impact of gas pressure and temperature on the aerodynamic surfaces of compressor blades of all stages. RESULTS: Based on thermal and structural analysis, the stress and temperature maps on compressor blades and vanes were obtained, taking into account the physical and mechanical properties of advanced materials and technologies of their processing. The safety factors of the components were established based on the assessment of their stress-strength reliability. Thanks to nomograms, the possibility of using the new materials and the technologies was confirmed in view of the permissible operating temperature and safety factors of blades. CONCLUSIONS: The proposed alternative materials and production technologies for the compressor blades and vanes meet the design requirements of the turbofan at lower manufacturing costs.

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Section: Twist Extrusionmentioning

confidence: 95%

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

Павленко¹,

Dvirnyk²,

Przysowa³

2020

Preprint

View full text Add to dashboard Cite

show abstract

“…Five TE passes were carried out, so the total relative shear deformation of the billet was 5.77. The porosity of the specimens was measured by the hydrostatic weighing method (GOST 18847-84) and by analysing the micrographs of metallographic specimens (GOST 9391-80) [45]. In the first case, the specimens were submerged into distilled water, whose temperature was measured by a mercury thermometer.…”

Section: Twist Extrusionmentioning

confidence: 99%

“…For the investigation of structure and the fractographic analysis of fracture surfaces, a NEOPHOT light microscope and a JEOL scanning electron microscope was used [46]. The average grain size in the samples after five TE passes was in the range of 200-500 nm for titanium alloys [45]. The grain size in the original material was 150-300 µm.…”

Section: Twist Extrusionmentioning

confidence: 99%

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

2020

View full text Add to dashboard Cite

Manufacturing costs, along with operational performance, are among the major factors determining the selection of the propulsion system for unmanned aerial vehicles (UAVs), especially for aerial targets and cruise missiles. In this paper, the design requirements and operating parameters of small turbofan engines for single-use and reusable UAVs are analysed to introduce alternative materials and technologies for manufacturing their compressor blades, such as sintered titanium, a new generation of aluminium alloys and titanium aluminides. To assess the influence of severe plastic deformation (SPD) on the hardening efficiency of the proposed materials, the alloys with the coarse-grained and submicrocrystalline structure were studied. Changes in the physical and mechanical properties of materials were taken into account. The thermodynamic analysis of the compressor was performed in a finite element analysis system (ANSYS) to determine the impact of gas pressure and temperature on the aerodynamic surfaces of compressor blades of all stages. Based on thermal and structural analysis, the stress and temperature maps on compressor blades and vanes were obtained, taking into account the physical and mechanical properties of advanced materials and technologies of their processing. The safety factors of the components were established based on the assessment of their stress-strength characteristics. Thanks to nomograms, the possibility of using the new materials in five compressor stages was confirmed in view of the permissible operating temperature and safety factor. The proposed alternative materials for compressor blades and vanes meet the design requirements of the turbofan at lower manufacturing costs.

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The Main Defects and Ways to Improve the Quality of Layer-by-Layer Sintered Gas Turbine Parts

Ткач

Павленко

Dvirnyk

et al. 2022

Lecture Notes in Networks and Systems

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Effect of Porosity Parameters on the Strength of Gas Turbine Compressor Blades Made of Titanium Alloys

Cited by 3 publications

References 14 publications

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

Advanced Materials and Technologies for Compressor Blades of Small Turbofan Engines

The Main Defects and Ways to Improve the Quality of Layer-by-Layer Sintered Gas Turbine Parts

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