2012 - Europe Direct Iasi

X. 22.
Title
EUROINVENT 2012
this research is to extend the lifetime of cam - follower by using
a common, cheap and easily processed material, which coated
through thermal barrier by modern methods of submission, are
intended to prevent spallation, improving mechanical behavior
and wear resistance. The deposited layer comes as a filler
element to the basic material and between these two can speak of
a limit of separation or interface more or less clearly delineated.
This research presents a new concept of thermal barrier coating
for the prevention of delamination of the sprayed layer. This
consists in an adherent layer of NiMoAl (90-5-5) and a top coat
of Al 2O 3-TiO 2, deposited by atmospheric plasma spraying (APS)
on specimens which the camshaft are made.
Studies and research on increases wear and corrosion resistances
of surfaces turbine blades per thermal deposition methods
Authors Pintilei Geanina Laura
Institution
Description
Technical University “Gh. Asachi” of Iaşi,
Faculty of Mechanical Engineering,
street Dimitrie Mangeron, no 29, zip 700050, ROMANIA
The achievement of the ceramic layer on the turbine blades for
aircraft engine is now a usual method for increasing strength and
durability of the blades. Turbine blades for aircraft engine are
subdued, during functioning, to thermal and mechanical stresses,
which can lead to their deterioration. Thermal barrier coatings
(TBCs) are used to isolate the components of gas turbines which
are submitted excessively temperatures and allows these coatings
to take action as a thermal barrier.
Turbine blades for aircraft engine are subdued, during
functioning, to thermal and mechanical stresses, which can lead
to their deterioration.
The purpose of this research is to extend the lifetime of turbine
blades by using a common, cheap and easily processed material,
which coated through thermal barrier by modern methods of
submission are intended to prevent spallation, improving thermomechanical
behavior and performance at high temperatures.
The thermal barrier consists in an adherent layer of NiMoAl (90-
5-5) sprayed with electric arc and a top coat of ZrO2/20%Y 2O 3,
deposited by atmospheric plasma spraying (APS) on specimens
of Ni base superalloy, of which the aircraft turbine blades are
made engine Tumanski R13 which equips the MIG 21.
X. 23.
Title Composite modular strenght –low profile partial foot prosthetic
Authors Dimitriu Bogdan Ioan
Institution University “Gheorghe Asachi” Iasi, Mechanical Faculty –
Innovative Researches
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