UNITIZED BUILD ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING USING ADDITIVE MANUFACTURING TECHNIQUE AND ASSEMBLY FOR A UNITIZED BUILD ASSEMBLY FOR A GAS TURBINE ENGINE

UNITIZED BUILD ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING USING ADDITIVE MANUFACTURING TECHNIQUE AND ASSEMBLY FOR A UNITIZED BUILD ASSEMBLY FOR A GAS TURBINE ENGINE

A unitized build assembly for a gas turbine engine (100) includes an exhaust duct (108), a hot section (106, 206, 306) with a locking structure and including a combustor (112, 212) and turbine section. The hot section (106, 206, 306) at least partially circumferentially surrounds the exhaust duct (1...

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Bibliographische Detailangaben
Hauptverfasser: BOYER, Jesse R, MORGANSON, David W, BINEK, Lawrence A
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
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Zusammenfassung:A unitized build assembly for a gas turbine engine (100) includes an exhaust duct (108), a hot section (106, 206, 306) with a locking structure and including a combustor (112, 212) and turbine section. The hot section (106, 206, 306) at least partially circumferentially surrounds the exhaust duct (108). The build assembly includes a compressor section (104, 204, 304) with an interface structure and is proximal to the hot section (106, 206, 306). The hot section (106, 206, 306) at least partially circumferentially surrounds at least part of the compressor section (104, 204, 304) and the locking structure is configured to engage the interface structure to limit movement of the hot section (106, 206, 306) relative to the compressor section (104, 204, 304).