The Impact of the Gas Turbine Blade Heating Temperature in the Presence of Aviation Kerosene on Coating and Alloy Microstructure

Bogdan, Mariusz; Kułaszka, Artur; Zasada, Dariusz

doi:10.2478/ama-2025-0018

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The Impact of the Gas Turbine Blade Heating Temperature in the Presence of Aviation Kerosene on Coating and Alloy Microstructure

Acta Mechanica et Automatica

Volume 19 (2025): Issue 1 (March 2025)

By: Mariusz Bogdan , Artur Kułaszka and Dariusz Zasada

Open Access

|Mar 2025

Figures & Tables

Example of blade convex (suction face) surfaces

Fig. 2.

Sample roughness and undulation profile – new blade

Fig. 3.

Impact of heating temperature on roughness profile changes – Ra

Fig. 4.

Impact of heating temperature on roughness profile changes – Rz

Blade surface morphology - new, not heated: a) BSE-TOPO; b) BSE

Blade surface morphology at 1123 K: a) BSE-TOPO; b) BSE

Blade surface morphology at 1223 K: a) BSE-TOPO; b) BSE

Blade surface morphology at 1323 K: a) BSE-TOPO; b) BSE

Blade surface morphology at 1423 K: a) BSE-TOPO; b) BSE

Blade surface morphology at 1523 K: a) BSE-TOPO and b) BSE

Blade surface morphology: a) new; b) 1123 K; c) 1223 K; d) 1323 K; e) 1423 K; f) 1523 K

Percentage share by weight of elements on the surface of tested blades – (SEM/EDS)

Percentage share of elements on the surface of tested blades – element mapping method

Total percentage share of oxides measured on the surfaces of tested blades

Percentage share of individual oxides measured on the surfaces of tested blades

Blade coating microstructures by heating temperature: a) new; b) 1123 K; c) 1223 K; d) 1323 K; e) 1423 K; f) 1523 K

Changes in the thickness of the external and diffusion coating exposed to different temperatures

Chemical composition of the external coating part of a new blade and heated blades

Chemical composition of the diffusion coating part of a new blade and heated blades

Blade alloy grain size by heating temperature: a) new; b) 1123 K; c) 1223 K; d) 1323 K; e) 1423 K; f) 1523 K

The dependence of a change in the average blade alloy grain size on heating temperature, expressed by an equivalent diameter of a circle with an area equal to the grain surface area

Blade alloy phase γ’ precipitate morphology by heating temperature: a) new; b) 1123 K; c) 1223 K; d) 1323 K; e) 1423 K; f) 1523 K

Percentage precipitate content of individual phase γ' molecule size classes in the alloy

Dependence of the average phase γ' precipitation in the alloy

Phase y’ precipitate microstructure of a new blade and heated blades (20000x zoom) – with visible coagulation, change of shape from cubic to irregular and phase precipitate undulation

Chemical composition of the superalloy used in the present study (wt_%)

C	Mn	Si	Cr	Co	Mo	W	Al	B	Fe	Ni
max	max	max						max		Rest
0.1	0.3	0.6	9.0	14.0	10.3	5.0	4.5	0.02	4.0	Rest

DOI: https://doi.org/10.2478/ama-2025-0018 | Journal eISSN: 2300-5319 | Journal ISSN: 1898-4088

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Language: English

Page range: 153 - 163

Submitted on: Jul 15, 2024

Accepted on: Nov 30, 2024

Published on: Mar 31, 2025

Published by: Bialystok University of Technology

In partnership with: Paradigm Publishing Services

Publication frequency: 4 issues per year

Keywords:

Related subjects:

Electrical engineering,

Electronics,

Mechanical engineering,

Mechanics,

Bioengineering and biomedical engineering,

Biomechanics,

Civil engineering,

Environmental engineering

© 2025 Mariusz Bogdan, Artur Kułaszka, Dariusz Zasada, published by Bialystok University of Technology
This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 License.

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The Impact of the Gas Turbine Blade Heating Temperature in the Presence of Aviation Kerosene on Coating and Alloy Microstructure

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Chemical composition of the superalloy used in the present study (wt_%)

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