United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Gary M Stetson

Gabriel L Suciu

Glenn Levasseur

Daniel Bernard Kupratis

Joseph Brent Staubach

James W Norris

James D Hill

Om Parkash Sharma

A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.

Operability geared turbofan engine including compressor section variable guide vanes

A gas turbine engine has a fan which includes a plurality of fan blades that are rotatable about an axis, and a compressor section, where the combustor section includes a first compressor and a second compressor aft of the first compressor. At least one first variable guide vane controls operation of the first compressor and at least one second variable guide vane controls operation of the second compressor. A combustor is in fluid communication with the compressor section and a turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

A gas turbine engine has a variable overall pressure rate ('OPR'). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR.

Gas turbine engine with variable overall pressure ratio

A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section.

Reverse cavity blade for a gas turbine engine

A rotor blade for a gas turbine engine includes a bowed surface on a tip region of the suction side thereof. The curvature of the bowed surface progressively increases toward the tip of the blade. The bowed surface results in a reduction of tip leakage through a tip clearance from the pressure side to the suction side of the blade and reduces mixing loss due to tip leakage.

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Tolland, CT, United States of America

Gary M Stetson