GAS TURBINE ENGINE WITH HEAT PIPE SYSTEM AND CORRESPONDING METHOD FOR BOWED ROTOR AVOIDANCE

GAS TURBINE ENGINE WITH HEAT PIPE SYSTEM AND CORRESPONDING METHOD FOR BOWED ROTOR AVOIDANCE

A gas turbine engine (20) includes a rotor section (55) proximate to a combustor section (26), where the rotor section (55) is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine (20) also includes a heat pipe system (200;300;400;500;600;...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: PEARSON, Matthew Robert, SUCIU, Gabriel L, URBAN, Justin R
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
Online-Zugang:Volltext bestellen
Tags: Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
Beschreibung
Zusammenfassung:A gas turbine engine (20) includes a rotor section (55) proximate to a combustor section (26), where the rotor section (55) is subject to bowing effects due to thermal differences and heat transfer at engine shutdown. The gas turbine engine (20) also includes a heat pipe system (200;300;400;500;600;700). The heat pipe system includes one or more heat pipes (202;302A,302B;402A,402B;502A,502B) installed between an upper portion (102) of the rotor section (55) and a lower portion (104) of the rotor section (55). The heat pipe system (200;300;400;500;600;700) is operable to accept heat at a hot side (306A,306B;406A,406B;506A,506B) of the heat pipe system at the upper portion (102), flow heat from the hot side to a cold side (308A,308B;408A,408B;508A,508B) of the heat pipe system, and reject heat from the cold side of the heat pipe system at the lower portion (104) to reduce a thermal differential between the upper portion (102) and the lower portion (104) at engine shutdown.