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Equivalent Heat Load Test on Hot Aircraft Engine Components

100%

Mróz M. , Orłowicz A. W. , Tupaj M. , Lenik M.

tom Vol. 23, iss. 1

34--36

The paper presents the assumptions and methodology for investigating equivalent heat load testing of hot aircraft engine components. The basic heat loads occurring in an aircraft engine during aircraft flight are characterised. Diagrams of the proposed heat loads are presented, together with the number of cycles, and a test bench is characterised and shown to enable equivalent heat load testing of aircraft engine components.

Analiza właściwości powłokowych barier cieplnych natryskiwanych płomieniowo

100%

Czupryński A. , Ozgowicz A.

2014

tom R. 86, nr 12

9--19

W artykule porównano wyniki badań dotyczących właściwości eksploatacyjnych powłok ceramicznych natryskiwanych płomieniowo, materiałami ceramicznymi tlenkowymi w postaci proszku na osnowie tlenku aluminium Al2O3 oraz tlenku cyrkonu ZrO2, na podłoże z konstrukcyjnej stali niestopowej S235JR. Oceny dokonano w oparciu o badania metalograficzne, przyczepności powłoki do podłoża, odporności na ścieranie, odporności na zużycie erozyjne oraz udar cieplny.

This article compares the results of studies on the operational properties of the flame sprayed ceramic coatings, ceramics oxide powder on the base of aluminum oxide and zirconium oxide Al2O3 ZrO2, on the ground of non-alloy structural steel S235JR. The assessments were based on metallographic examination, the adhesion, abrasion resistance, resistance to erosive wear and thermal shock.

Measurement of residual stress in plasma-sprayed TBC with a gradient of porosity and chemical composition

67%

Moskal G. , Swadźba L. , Rzychoń T.

2007

tom Vol. 23, nr 2

31-34

Purpose: The purpose of the research was identification of the residual stress in the top coat of different type of thermal barrier coating with gradient of chemical composition and gradient of porosity. Design/methodology/approach: The APS technique was used to deposition of gradient coating. As a bond coat the NiCrAlY overlay coating was applied. Top-coat consist in the case of gradient of porosity - YSZ with different thickness and porosity and in the case of chemical composition gradient YSZ with AMDRY 365-2 powder. The research allowed the identification of qualitative and quantitative phase constitution of top coat and residual stress measurement by sin square Psi method form surface of coatings. Findings: It was found that the dominant phase in all the top coats was tetragonal zirconia with minor addition of monoclinic type of ZrO2 and in the case of residual stress the tensile conditions was observed in the case of gradient porosity and compressive stresses in the case of chemical gradient. Research limitations/implications: Characterization of stress level in gradient TBC's give possibility description of degradation mechanism of barrier coating. Practical implications: The results obtained allow the determination of the degree of life-time lost of the TBC system used as protection for creep resistant alloys. Originality/value: The results obtained are valuable contribution to the development of new type of TBC. They enable the identification of the degradation mechanisms in YSZ / MCrAlY / substrate system.

Structure and properties of TBC coatings obtained on the nickel base superalloys by a thermal spraying method.

51%

Swadźba L. , Hetmańczyk M. , Mendala B. , Dudek S. , Szala J.

tom R. XIX, nr 4

1061-1066

Results of investigations on obtaining the thermal barrier coatings (TBC) and their properties have been presented in the article. Coatings were formed by a thermal spraying method using a A3000 system controlled by computer and with a robot. For spraying the following materials: ZrO2xY2O3 and MeCrAlY as an interlayer were used. The coating structure examinations were made. Powder morphology was determined by the scanning microscope method. Tests by the thermal shock method were conducted in the air atmosphere by heating the specimens to 1200 degrees centigrade for 15 min. and cooling to 250 degrees centigrade for 5 min. Hot corrosion resistance tests were conducted at 900 degrees centigrade in the Na2SO4 medium. Tests showed low resistance of TBC coatings to that type of corrosion. The TBC coatings were formed on the combustion chamber elements.