Experimental Evaluation of Abradable Seal Performance at High Temperature

Dadouche, Azzedine; Conlon, Martin J.; Dmochowski, Waldemar; Liko, Brian; Bedard, J.-P.

doi:10.1115/gt2008-51228

Cited by 15 publications

(11 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the context of turbomachinery, one should mention the pioneering work [7] on wear mechanisms in gas turbines as well as the work of Schmid [8] which will be our main source of information regarding the phenomenology of abradable materials. Recently, experimental investigations on the dynamic characterization of abradable coatings within a simulated turbomachine environment were reported with respect to: a high relative interaction speed [9] (from 100 to 500 m/s), elevated temperatures [10] (up to 600 ı C) as well as a combination of high interaction speed and elevated temperatures [11,12]. While the influence of thermal conditions has long been investigated [13], experimental work carried out by industrials is rarely published.…”

Section: Phenomenology Of Abradable Wearmentioning

confidence: 99%

Abradable Coating Removal in Turbomachines: A Macroscopic Approach Accounting for Several Wear Mechanisms

Berthoul

Batailly

Legrand

et al. 2015

Volume 7B: Structures and Dynamics

View full text Add to dashboard Cite

Abradable materials are widely used as a coating within compressor and turbine stages of modern aircraft engines in order to reduce operating blade-tip/casing clearances and thus maximize the engine energy efficiency. However, recent investigations revealed that the interaction between a blade and these materials may threaten blades structural integrity. Consequently, there is a need for a better understanding of the physical phenomena at play and for an accurate modelling of the interaction in order to predict hazardous events. The cornerstone of related numerical investigations lies in the modelling of the abradable coating removal due to the blade/abradable coating interaction and the associated contact forces along the contact interface. In this context, this article presents a macroscopic model for abradable coating removal accounting for key wear mechanisms including adhesive wear, abrasive wear, micro-rupture wear and machining wear. It is coupled with an in-house numerical strategy for the modelling of full 3D blade/abradable coating interactions within turbomachines and applied to an aircraft engine. Numerical results are compared with respect to existing models and available experimental data. The applicability of the proposed model for 3D interaction simulations is underlined as well as the consistency of the obtained results with experimental observations.

show abstract

Section: Phenomenology Of Abradable Wearmentioning

confidence: 99%

Abradable Coating Removal in Turbomachines: A Macroscopic Approach Accounting for Several Wear Mechanisms

Berthoul

Batailly

Legrand

et al. 2015

Volume 7B: Structures and Dynamics

View full text Add to dashboard Cite

show abstract

“…Several investigations on the static characterization of abradable coatings [23,11] as well as abradability investigations carried out statically, or at very low speed, are available [31,32] in addition to a few scratch tests [15,16]. Recently, experimental investigations on the dynamic characterization of abradable coatings within a simulated turbo-machinery environment were reported with respect to: a high relative interaction speed (from 100 m/s to 500 m/s) [5,28], elevated temperatures (up to 600 • C) [6] as well as a combination of high interaction speeds and elevated temperatures [17,22]. While the influence of thermal conditions has long been explored [21], experimental works carried out by manufacturers are rarely published.…”

Section: Introductionmentioning

confidence: 99%

Phenomenological modeling of abradable wear in turbomachines

Berthoul

Batailly

Stainier

et al. 2018

Mechanical Systems and Signal Processing

View full text Add to dashboard Cite

International audienceAbradable materials are widely used as coatings within compressor and turbine stages of modern aircraft engines in order to reduce operating blade-tip/casing clearances and thus maximize energy efficiency. However, rubbing occurrences between blade tips and coating liners may lead to high blade vibratory levels and endanger their structural integrity through fatigue mechanisms. Accordingly, there is a need for a better comprehension of the physical phenomena at play and for an accurate modeling of the interaction, in order to predict potentially unsafe events. To this end, this work introduces a phenomenological model of the abradable coating removal based on phenomena reported in the literature and accounting for key frictional and wear mechanisms including plasticity at junctions, ploughing, micro-rupture and machining. It is implemented within an in-house software solution dedicated to the prediction of full three-dimensional blade/abradable coating interactions within an aircraft engine low pressure compressor. Two case studies are considered. The first one compares the results of an experimental abradable test rig and its simulation. The second one deals with the simulation of interactions in a complete low-pressure compressor. The consistency of the model with experimental observations is underlined, and the impact of material parameter variations on the interaction and wear behavior of the blade is discussed. It is found that even though wear patterns are remarkably robust, results are significantly influenced by abradable coating material properties

show abstract

“…Then to optimize the material selection and structural design of the metal honeycomb and labyrinth blade, an understanding of their tribological behavior is required. At present, Pratt & Whitney of America (Bill and Shiembob, 1977), Sulzer Innotec of Switzerland (Bardi et al, 2008), University of Sheffield (Stringer and Marshall, 2012), Alstom, the National Research Council Canada (Dadouche et al, 2008), Ohio State University (Padova et al, 2006), et al have developed their own abradable test equipment for abrasion interaction investigation and abradability performance evaluation of abradable seal materials. The most distinguishing characteristic of the new abradable test equipment is that it is able to simulate the high-speed and high-temperature working conditions which are similar to those of actual engines and other turbine or compressor machines.…”

Section: Introductionmentioning

confidence: 99%

Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application

Zhang

Guo³

et al. 2016

J. Zhejiang Univ. Sci. A

View full text Add to dashboard Cite

Abstract:The labyrinth-honeycomb seal has been widely used in gas turbine engines as an abradable gas path seal to protect the rotor from wear and damage in rubbing interaction. It usually works with a stepped labyrinth because the knife-edged tips could produce a special dynamic sealing system, and then the minimum clearance is possible between the rotor and stationary component. To investigate the high-speed rubbing behavior between a Hastelloy-X honeycomb material and a GH4169 double stepped labyrinth, nine rubbing tests were conducted using a high-speed abrasion test rig while the blade tip speed varied from 150 to 450 m/s, and the incursion rate from 120 to 360 μm/s. The abradability of honeycomb made from Hastelloy-X was fully verified by analyzing the visual rubbing observations, rubbing forces, and impact acceleration. It is shown that compression deformation happens to the honeycomb material during the rubbing process with the labyrinth blade except for a simple cutting mechanism, which is mainly affected by the parameter of incursion rate. Thermal ablation and oxidation were the main damage occurring on the labyrinth tip and appeared more obviously at a higher blade tip speed. Rubbing forces and impact acceleration were obtained from a piezoelectric dynamometer and acceleration sensor during the rubbing process. At a blade tip speed of 300 m/s and incursion rate of 360 μm/s, radial and tangential forces show their maximum values of 716 N and 871 N, respectively. The peak value of acceleration presents 341g with the highest blade tip speed of 450 m/s and the highest incursion rate of 360 μm/s. All testing results provide a great deal of effective information on high-speed rubbing behavior for the abradablility evaluation of a honeycomb.

show abstract

Experimental Evaluation of Abradable Seal Performance at High Temperature

Cited by 15 publications

References 4 publications

Abradable Coating Removal in Turbomachines: A Macroscopic Approach Accounting for Several Wear Mechanisms

Abradable Coating Removal in Turbomachines: A Macroscopic Approach Accounting for Several Wear Mechanisms

Phenomenological modeling of abradable wear in turbomachines

Investigation of high-speed rubbing behavior of labyrinth-honeycomb seal for turbine engine application

Contact Info

Product

Resources

About