GAS TURBINE ENGINES AND CORRESPONDING MAINTENANCE METHOD
A gas turbine engine (20) includes a compressor (44, 52), a combustor (56) fluidly connected to the compressor (44, 52) via a flow path, and a turbine (46, 54) fluidly connected to the combustor (56) via the flow path. At least one multi-piece structure (100; 200; 300) is disposed within the flow pa...
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Format: | Patent |
Sprache: | eng ; fre ; ger |
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Zusammenfassung: | A gas turbine engine (20) includes a compressor (44, 52), a combustor (56) fluidly connected to the compressor (44, 52) via a flow path, and a turbine (46, 54) fluidly connected to the combustor (56) via the flow path. At least one multi-piece structure (100; 200; 300) is disposed within the flow path such that the multi-piece structure (100...300) at least partially radially spans the flow path. The at least one multi-piece structure (100...300) includes a fore portion (102; 202; 302; 402; 502) defining a leading edge (106; 206; 306), a consumable aft portion (104; 204; 304; 404; 504) defining a trailing edge (108; 208; 308), a pressure surface (260; 360) at least partially defined by a first surface of the fore portion (102...502) and a first surface of the consumable aft portion (104...504), and a suction surface (270; 370) at least partially defined by a second surface of the fore portion (102...502) and a second surface of the consumable aft portion (104...504). |
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