Unducted, counterrotating gearless front fan engine
First Claim
1. A high bypass ratio gas turbine engine comprising:
- a core engine effective for generating combustion gases passing through a main flow path;
a power turbine aft of said core engine and including first and second counter rotatable interdigitated turbine blade rows effective for counterrotating first and second drive shafts, respectively;
an unducted fan section forward of said core engine including a first fan blade row connected to said first drive shaft and a second fan blade row axially spaced aftward from said first fan blade row and connected to said second drive shaft, anda booster compressor axially positioned between said first and second fan blade rows and including a plurality of first compressor blade rows connected to said first drive shaft and a plurality of second compressor blade rows connected to said second drive shaft.
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Accused Products
Abstract
A gas turbine engine having a core for generating combustion gases, a power turbine, an unducted fan section and a booster compressor. The power turbine includes two counterrotating turbine blade rows which are interdigitized and serve to rotate counterrotating first and second drive shafts, respectively. The unducted fan section also includes counterrotating spaced apart variable pitch fan blade rows which are respectively connected to the first and second drive shafts. A booster compressor is axially positioned between the spaced apart fan blade rows. The booster compressor likewise includes first and second blade rows which are counterrotating and interdigitated and are likewise driven by the first and second drive shafts. The engine is supported by two stationary support frames to permit the nacelle to be nonstructural. The core engine is a modular unit so that it can be separable from the rest of the engine.
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Citations
24 Claims
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1. A high bypass ratio gas turbine engine comprising:
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a core engine effective for generating combustion gases passing through a main flow path; a power turbine aft of said core engine and including first and second counter rotatable interdigitated turbine blade rows effective for counterrotating first and second drive shafts, respectively; an unducted fan section forward of said core engine including a first fan blade row connected to said first drive shaft and a second fan blade row axially spaced aftward from said first fan blade row and connected to said second drive shaft, and a booster compressor axially positioned between said first and second fan blade rows and including a plurality of first compressor blade rows connected to said first drive shaft and a plurality of second compressor blade rows connected to said second drive shaft. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21)
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22. A high bypass ratio gas turbine engine comprising:
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a core engine; a power turbine aft of said core engine; an unducted fan section forward of said core engine coupled to said power turbine and comprising fan blades; a booster compressor axially positioned between at least a part of said fan section and said core and including booster compressor blades; means for varying the pitch on said fan blades, and means for varying the pitch on said booster compressor blades, whereby the speed of the engine can be controlled through varying the pitch on both the fan and the booster compressor blades while maintaining the power level of the engine. - View Dependent Claims (23, 24)
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Specification