General Electric Company

Unison Industries, Inc.

General Electric Company Polska Sp. Z O.o.

Vishnu Vardhan Venkata Tatiparthi

Keith Blodgett

Ravindra Shankar Ganiger

David Raju Yamarthi

Shiloh Montegomery Meyers

Subrata Nayak

Milind Chandrakant Dhabade

Ramana Reddy Kollam

Vasanth Kumar Balaramudu

Saurya Ranjan Ray

Sai Venkata Kathik Saripella

Arthur William Sibbach

Nitesh Jain

Paul Hadley Vitt

Vidyashankar Ramasastry Buravalla

Gary Willard Bryant, Jr

Paul Mathew

Michael Hogan

Sesha Subramanian

Francesco Bertini

Lyle D Dailey

Vaishnav Raghuvaran

Douglas Lorrimer Armstrong

Raghuveer Chinta

Nagashiresha G

Sai Venkata Karthik Saripella

Hari K Meka

Nuthi Srinivas

John Joseph

Avinash Natarajan

Michał Tomasz Kuropatwa

Sai Raju Ippili

Daniel O'Brien

Prateek Mathur

A turbine airfoil comprises an airfoil defining a leading edge, a trailing edge, a root portion, a tip portion, a chord line defining a chord length of the airfoil, a suction side surface extending in a spanwise direction from the root portion to the tip portion and in a flow-wise direction between the leading edge and the trailing edge, and a throat line extending spanwise along the suction side surface from the root portion to the tip portion. The turbine airfoil further includes a plurality of micro-riblet patches defined along the suction side surface aft of the throat line where each micro-riblet patch of the plurality of micro-riblet patches extends in the flow-wise direction between the throat line and the trailing edge.

Suction side micro-riblet patches for a turbine airfoil

Systems, apparatus, articles of manufacture, and methods are disclosed to improve fan operability control using smart materials. An engine comprising an engine surface in an airflow path, a sensor positioned on the engine surface, and a smart-material-based feature positioned on the engine surface, the smart-material-based feature triggered to modify the airflow path when the sensor outputs an indication of a detected deviation from a reference value of an operating parameter of the engine.

Methods and apparatus to improve fan operability control using smart materials

A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

Air guide for a gas turbine engine

An air turbine starter having a housing, a turbine, a drive shaft, and at least one vane. The housing having an inlet, an outlet and a curvilinear flow path extending between the inlet and the outlet. The at last one vane is located within a portion of the curvilinear flow path, and includes an outer wall extending between a root and a tip in a span-wise direction and between a leading edge and a trailing edge in a chord-wise direction. In one aspect, the vane is arranged to define an acute axial angle that is non-constant in the chord-wise or span-wise direction. In another aspect, the vane is arranged to define an acute tangential angle that is non-constant in the chord-wise or span-wise direction.

Air turbine starter with shaped vanes

An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.

Airfoil assembly with tensioned blade segments

An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.

Airfoil assembly with an internal reinforcement structure

Methods, apparatus, systems, and articles of manufacture are to control air flow separation of an engine. An example turbofan includes a nacelle having an outer lip surface, an inner lip surface, a first opening and a second opening, the first opening coupled to a first region forward of a fan of the turbofan, the second opening coupled to a second region aft of the fan, the nacelle including a first pressure sensor coupled to the outer lip surface, a second pressure sensor coupled to the inner lip surface, and an actuator, and a conduit coupled to the actuator, the conduit configured to have a first end and a second end, the first end coupled to the first opening, the second end coupled to the second opening.

Methods and apparatus to control air flow separation of an engine

A turbine engine including a fan, a nacelle circumscribing at least the fan, a compressor section downstream of the fan, and a conduit defined, at least in part, by the nacelle. The conduit includes a first opening at the compressor section, a second opening downstream of the fan and upstream of the compressor section, and a third opening upstream of the fan. Pressure sensors coupled to the nacelle are communicatively coupled to at least one actuator. The at least one actuator can adjust airflow between the first opening and the second opening, or between the first opening and the third opening. The pressure sensors can provide outputs for generating commands that control the at least one actuator.

Methods and apparatus to detect air flow separation of an engine

An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.

Methods, apparatus, systems, and articles of manufacture are disclosed to detect air flow separation of an engine. An example apparatus includes hardware, and memory including instructions that, when executed, cause the hardware to at least determine an inlet flow separation parameter based on a first pressure value from a first pressure sensor included in a nacelle of a turbofan and a second pressure value from a second pressure sensor included in the nacelle, determine a severity level parameter based on the inlet flow separation parameter, the severity level parameter based on a difference between the first pressure value and the second pressure value, and adjust a contribution of airflow from aft of a fan of the turbofan based on the severity level parameter.

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Bengaluru, India

Vishnu Vardhan Venkata Tatiparthi