TURBINE ENGINE WITH THERMAL SEAL

A turbine engine (16) with a casing (52) including opposing surfaces (48, 58) and a manifold opening (76) passing through the surfaces. A surface cooler (50) is provided adjacent one of the surfaces (48, 58). A cooler manifold (80) passes through the manifold opening (76). A seal (100) is provided b...

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Bibliographische Detailangaben
Hauptverfasser:	MCCANN, Daniel Scott, MILLWARD, David William, SCHMITT, Joseph Richard, DREISCHARF, Derek Thomas, LUSCHEK, Bernard Albert
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine engine (16) with a casing (52) including opposing surfaces (48, 58) and a manifold opening (76) passing through the surfaces. A surface cooler (50) is provided adjacent one of the surfaces (48, 58). A cooler manifold (80) passes through the manifold opening (76). A seal (100) is provided between the surface cooler (50) and the casing (52). At least one bolt (103a) is used to secure the surface cooler (50) to the casing (52) with the seal (100) in between.