GAS TURBINE ENGINE WITH SHORTENED MID SECTION
An industrial gas turbine engine (10) rated for at least 75 MW maximum output, including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section length (112) between a trailing edge (28) of a last row of compressor airfoils (20, 22) and a leading edge (5...
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Main Author | |
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Format | Patent |
Language | English French German |
Published |
15.07.2015
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Subjects | |
Online Access | Get full text |
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Summary: | An industrial gas turbine engine (10) rated for at least 75 MW maximum output, including: a can annular combustion assembly (80); and a single rotor shaft (114); wherein a combustion section length (112) between a trailing edge (28) of a last row of compressor airfoils (20, 22) and a leading edge (54) of first row of turbine blades (56) is less than 20% of an engine length (154) between a leading edge (26) of a first row of compressor airfoils and a trailing edge (66) of a last row of turbine airfoils (60, 62). |
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Bibliography: | Application Number: EP20130753781 |