REVERSE CORE GEAR TURBOFAN
First Claim
1. A gas turbine engine comprising:
- a fan at an axially outer location, said fan rotating about an axis of rotation;
said fan delivering air into an outer bypass duct, and across a booster fan positioned radially inwardly of said outer bypass duct, said booster fan delivering air into a radially middle duct, and said booster fan delivering air across a cold turbine into a radially inner core duct;
air from said inner core duct being directed into a compressor, and then flowing axially in a direction back toward said fan through a combustor section, and across a core turbine section, and then being directed into said middle duct; and
a gear reduction for driving said fan from a fan drive turbine section.
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Accused Products
Abstract
A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.
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Citations
23 Claims
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1. A gas turbine engine comprising:
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a fan at an axially outer location, said fan rotating about an axis of rotation; said fan delivering air into an outer bypass duct, and across a booster fan positioned radially inwardly of said outer bypass duct, said booster fan delivering air into a radially middle duct, and said booster fan delivering air across a cold turbine into a radially inner core duct; air from said inner core duct being directed into a compressor, and then flowing axially in a direction back toward said fan through a combustor section, and across a core turbine section, and then being directed into said middle duct; and a gear reduction for driving said fan from a fan drive turbine section. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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21. A method of operating a gas turbine engine comprising the steps of:
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(a) operating a turbine section having blades with a radially outermost extent, and a flow diverter that is operable to divert air radially inwardly of the radially outermost extent of the turbine blades, or allow air to pass radially outwardly of the radially outermost extent of the turbine blades; and (b) positioning said flow diverter to increase or decrease the amount of gas passing across that turbine rotor to increase or decrease a power output by said turbine rotor. - View Dependent Claims (22, 23)
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Specification