Explanation of the mechanisms of unsteady gas flow through the turbocharger seal system, including thermal and structural interactions

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F23%3APU148642" target="_blank" >RIV/00216305:26210/23:PU148642 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1016/j.jppr.2023.05.003" target="_blank" >https://doi.org/10.1016/j.jppr.2023.05.003</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.jppr.2023.05.003" target="_blank" >10.1016/j.jppr.2023.05.003</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Explanation of the mechanisms of unsteady gas flow through the turbocharger seal system, including thermal and structural interactions

Popis výsledku v původním jazyce

Gas flow in the seal system can be expected during the operation of a turbocharger and is associated with negative effects on the quality of the lubricant or turbocharger efficiency. Gas flow also affects particulate matter production due to lubricant entrainment in the compressor or turbine. The prediction of gas flow rates depends on many design parameters and the operating conditions of the turbocharger, but sufficiently accurate descriptions of the gas flow mechanisms and their quantification depending on the operating conditions have not yet been presented. The proposed computational approach simultaneously solves the gas dynamics in the seal system, the heat transfer in the turbocharger rotor-bearing system and the dynamics of the seal rings and rotor, including the bearings. The computational model for the turbocharger of a heavy-duty vehicle engine is experimentally validated. Two mechanisms have major influences on gas mass flow: the gas flow through the thin gap between the moving ring and groove and the flow through the ring gap. The results show that the importance of these mechanisms depends on several geometrical dimensions of the seal system and the operating conditions of the turbocharger, with a strong connection to the rotor dynamics and thermal load of the impellers. Influences involving rotor movement or rotor thermal conditions are crucial, and their non-inclusion limits the ability to correctly predict gas mass flow.

Název v anglickém jazyce

Explanation of the mechanisms of unsteady gas flow through the turbocharger seal system, including thermal and structural interactions

Popis výsledku anglicky

Gas flow in the seal system can be expected during the operation of a turbocharger and is associated with negative effects on the quality of the lubricant or turbocharger efficiency. Gas flow also affects particulate matter production due to lubricant entrainment in the compressor or turbine. The prediction of gas flow rates depends on many design parameters and the operating conditions of the turbocharger, but sufficiently accurate descriptions of the gas flow mechanisms and their quantification depending on the operating conditions have not yet been presented. The proposed computational approach simultaneously solves the gas dynamics in the seal system, the heat transfer in the turbocharger rotor-bearing system and the dynamics of the seal rings and rotor, including the bearings. The computational model for the turbocharger of a heavy-duty vehicle engine is experimentally validated. Two mechanisms have major influences on gas mass flow: the gas flow through the thin gap between the moving ring and groove and the flow through the ring gap. The results show that the importance of these mechanisms depends on several geometrical dimensions of the seal system and the operating conditions of the turbocharger, with a strong connection to the rotor dynamics and thermal load of the impellers. Influences involving rotor movement or rotor thermal conditions are crucial, and their non-inclusion limits the ability to correctly predict gas mass flow.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20301 - Mechanical engineering

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2023

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

Propulsion and Power Research

ISSN

2212-540X

e-ISSN

—

Svazek periodika

12

Číslo periodika v rámci svazku

2

Stát vydavatele periodika

CN - Čínská lidová republika

Počet stran výsledku

19

Strana od-do

180-198

Kód UT WoS článku

001037344800001

EID výsledku v databázi Scopus

2-s2.0-85162227726