General Electric Company

Other

Deepak Manohar Kamath

Mehdi Milani Baladi

Sridhar Adibhatla

Aspi Rustom Wadia

Michael J Epstein

Daniel Waslo

William Randolph Shinkle

Kenneth Foster Cook

Bruce Gunter Schings

Robert David Wittenbach

Scott Chandler Morton

Aidan William Clark

Todd James Buchholz

Robert Lawrence Mayer

Sergei A Jerebets

Alejandro Yatzail Perez Valadez

Sanjay Shridhar

Taylor J Rosenfeld

A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.

Turbofan engine's fan blade and setting method thereof

A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.

Cryogenic fuel system and method for delivering fuel in an aircraft

A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.

System for temperature and actuation control and method of controlling fluid temperatures in an aircraft

A method, system and program product comprise obtaining a user's username and password. A random key is generated for use as a master key. The master key is encrypted using the password to create an encrypted master key. A hash function is performed on the password to create a password hash. A random key is generated for use as a content key for encrypting the user's selected content. The content key is encrypted using the master key to create an encrypted content key. The selected content is encrypted using the content key to create encrypted content. The username, password hash, encrypted master key, first encrypted content key, and encrypted content is communicated to a server for storage in the user's account in which the possibility of decrypting at least the encrypted content by operations on the server is mitigated.

Method, system and program product for secure storage of content

Sensor-based, performance-seeking control of gas turbine engines is disclosed. An example method of controlling a gas turbine engine may include varying an engine input parameter while operating the gas turbine engine to produce a desired output, including measuring a pre-adjustment value of an engine operating parameter with an engine input parameter at an initial value, adjusting the engine input parameter to a current adjusted value, and measuring a post-adjustment value of the engine operating parameter. The method may include determining a future adjusted value of the engine input parameter and iteratively repeating the varying the engine input parameter operation and the determining the future adjusted value of the engine input parameter operation. The method may be performed while operating the gas turbine engine to produce a desired output.

Sensor-based performance-seeking gas turbine engine control

The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust performance measured at manufacture or overhaul. In one embodiment, the invention provides an analog speed signal to flight control apparatus. The invention may also be configured to provide a digital speed signal to engine power management control apparatus.

Speed modification system for gas turbine engine to allow trimming of excess

A method for detecting fault in a resolver generating a sine voltage and a cosine voltage. The method includes obtaining a sum of a square of the sine voltage and a square of the cosine voltage. The sum is filtered through a first filter having a first time constant to generate a first filter output. The sum is also filtered through a second filter having a second time constant to generate a second filter output. The first filter output and second filter output are compared to detect a fault in the resolver.

Growing community of inventors

Fairfield, OH, United States of America

Deepak Manohar Kamath