Labyrinth seals are often utilized in locations where contact seals cannot be utilized due to the large displacements of the rotating shaft. The performance evaluation of a labyrinth seal is very important to make sure that optimum performance of turbomachinery is attained. Performance parameters such as carryover coefficient, discharge coefficient were evaluated for a see through triangular tooth on stator labyrinth seal. This computational study investigates how flow conditions and seal parameter variations for see through tooth on stator triangular cavity labyrinth seals affect the value of the carryover coefficient and discharge coefficient. A Finite volume CFD commercial code was used to accomplish the above study. The influence of Reynolds number, rotational speed, seal radial clearance, pitch, tooth angle, tooth width are considered using the finite volume method of computational fluid dynamics. It was found that Reynolds number, high shaft speed and clearance have a significant effect on the carryover coefficient and the discharge coefficient. Clearance is the major influential parameter to be considered among all seal geometric parameters to optimize an ideal seal.

The master´s thesis concentrates on a project of steam turbine with controlled extraction points destined for a communal waste incineration plant. First, there the history of devices using steam as a moving medium is introduced and than follows the description of computing program, where the calculation was running. The master´s thesis subject consists in the thermodynamic project of turbine vaning, in basic project of gearbox including the check calculations and in technical economic comparison of single shaft and twin shaft constructional design. The design documentation is worked up according to the calculated outcomes and contains longitudinal section of turbine and dispositional turbine and gearbox settlement.

This master’s thesis deals with theme of turbocharger seals. The aims of a thesis are to compare a turbocharger seals used in PBS Turbo turbochargers and to describe a testing of a seals. Principle of turbocharging and types of turbocharger are described in fist part. Next point of the thesis is describing of a face seals and non-contacting seals. The main part of the thesis describes kinds and reasons of seals testing; also contains comparison between labyrinth seals and piston ring, comparison of seals of PBS Turbo’s turbochargers and assesses the impact of turbocharger angle on the tightness of the seal.

The labyrinth seal is a non-contact annular type sealing device used to reduce the internal leakage of the working fluid which is caused by the pressure difference between each stage in a turbomachine. Reducing the leakage mass flow rate of the working fluid through the labyrinth seal is desirable because it improves the efficiency of the turbomachine. The carry-over coefficient, based on the divergence angle of the jet, changed with flow parameters with fixed seal geometry while earlier models expressed the carry-over coefficient solely as a function of seal geometry. For both compressible and incompressible flows, the Reynolds number based on clearance was the only flow parameter which could influence the carry-over coefficient. In the case of incompressible flow based on the simulations for various seal geometries and operating conditions, for a given Reynolds number, the carry-over coefficient strongly depended on radial clearance to tooth width ratio. Moreover, in general, the lower the Reynolds number, the larger is the divergence angle of the jet and this results in a smaller carry-over coefficient at lower Reynolds numbers. However, during transition from laminar to turbulent, the carry-over coefficient reduced initially and once the Reynolds number attained a critical value, the carry-over coefficient increased again. In the case of compressible flow, the carry-over coefficient had been slightly increased if radial clearance to tooth width ratio and radial clearance to tooth pitch ratio were increased. Further, the carry-over coefficient did not considerably change if only radial clearance to tooth width ratio was decreased. The discharge coefficient for compressible and incompressible flows depended only on the Reynolds number based on clearance. The discharge coefficient of the tooth in a single cavity labyrinth seal was equivalent to that in a multiple tooth labyrinth seal indicating that flow downstream had negligible effect on the discharge coefficient. In particular, for compressible fluid under certain flow and seal geometric conditions, the discharge coefficient did not increase with an increase in the Reynolds number. It was correlated to the pressure ratio, Pr. Moreover, it was also related to the fact that the flow of the fluid through the constriction became compressible and the flow eventually became choked. At low pressure ratios (less than 0.7), Saikishan’s incompressible model deviated from CFD simulation results. Hence, the effects of compressibility became significant and both the carry-over coefficient compressibility factor and the discharge coefficient compressibility factor needed to be considered and included into the leakage model. The carry-over coefficient compressibility factor, phi, had two linear relationships with positive and negative slopes regarding the pressure ratios. This result was not associated with the seal geometry because the seal geometry ratios for each instance were located within the nearly same ranges. Further, the phi-Pr relationship was independent of the number of teeth regardless of single and multiple cavity labyrinth seals. The discharge coefficient compressibility factor, psi, was a linear relationship with pressure ratios across the tooth as Saikishan predicted. However, in certain flow and seal geometric conditions, Saikishan’s model needed to be modified for the deviation appearing when the pressure ratios were decreased. Hence, a modified psi-Pr relationship including Saikishan’s model was presented in order to compensate for the deviation between the simulations and his model.

Une des solutions envisagées par les motoristes pour améliorer le rendement des turbomoteurs consiste à réduire le jeu en fonctionnement dans les deux systèmes d’air des turbomachines. Plus particulièrement dans le système d’étanchéité d’air secondaire, la réduction du jeu entre les parties fixes et tournantes améliore le contrôle des étanchéités du moteur et les niveaux de refroidissement entre les différents modules des turbomoteurs, mais entraînent des interactions indésirables entre les différents composants. Les systèmes d’étanchéité dynamiques sont composés de joints labyrinthes couplés à un revêtement abradable sacrificiel en vis-à-vis, qui offre la particularité de s’user préférentiellement en préservant la majeure partie du système d’étanchéité en évitant une usure de la partie tournante. L’objectif de cette thèse est de reproduire et d’étudier, par l’intermédiaire d’un banc technologique haute vitesse spécialement conçu pour l’étude, les interactions labyrinthe-abradable appliquées au couple acier inoxydable/Al-Si 6%, dans des conditions de fonctionnement d’un turbomoteur. Une instrumentation spécifique est développée sur le banc et apporte à l’étude les données expérimentales manquantes visant à la caractérisation des interactions labyrinthe-abradable. Une analyse tribologique, basée sur le concept de troisième corps, est menée afin d’identifier les différents débits de matière puis de décrire les étapes successives des mécanismes d’usure (circuit tribologique) du revêtement Al-Si 6%. L’influence des paramètres de pilotage de l’interaction et de la géométrie du joint a été étudiée. Enfin, une étude statistique basée sur l’iconographie des corrélations, permet de modéliser le comportement global du système labyrinthe-abradable, d’identifier les paramètres influents du système et d’apporter des critères pour une potentielle surveillance des interactions. Ces travaux de thèse ont été réalisés dans le cadre d’une collaboration entre TURBOMECA Bordes (groupe SAFRAN), et le Laboratoire Génie Production (LGP) de Tarbes. / S of turbomachinery. Especially in the secondary air sealing system, the tight clearance between the stationary and rotating parts improves control of engine seals and cooling levels between the different modules of the engines but may cause undesirable interactions between the static and rotating components. Dynamic sealing systems are composed of labyrinth seals coupled to a sacrificial abradable coating, which can accommodate interactions to preserve the global geometrical seal integrity. The objective of this thesis is to study and reproduce, through a technological high speed test rig specifically designed for the study, the labyrinth-abradable interactions applied to stainless steel/Al-Si 6% couple, under similar turbo-engine operating conditions. A suitable instrumentation is developed on the test ring to complete missing experimental data to characterize abradable labyrinth interactions. A tribological study, based on the third body concept, is proposed to identify wear mechanisms process of the Al-Si 6% coating. The influence of interaction control parameters and the seal geometry was investigated. Finally, a statistical study, based on the iconography of the correlation, is proposed to model the overall labyrinth-abradable system behavior and to identify influential parameters of the system and provide suitable criteria to monitor labyrinth seal interactions. This work was achieved within the framework of cooperation between TURBOMECA Bordes (SAFRAN Group), and the Laboratoire Génie de Production (LGP) de Tarbes.