TURBINE ENGINE AIRFOIL WITH A CRUSH INITIATOR

Organization Name

Inventor(s)

Vidyashankar Ramasastry Buravalla of Bangalore (IN)

TURBINE ENGINE AIRFOIL WITH A CRUSH INITIATOR - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240318558 titled 'TURBINE ENGINE AIRFOIL WITH A CRUSH INITIATOR

The abstract describes a gas turbine engine with an airfoil that has at least one stiffener with a crush initiator to control deformation geometry in response to external forces.

Gas turbine engine with fan, compressor, combustor, and turbine sections in serial flow arrangement.
Airfoil in one of the sections with at least one stiffener and crush initiator to control deformation.
Stiffener has a deformation threshold and crush initiator determines deformation geometry.
Crush initiator responds to force exceeding the deformation threshold to control stiffener deformation.

Potential Applications: - Aerospace industry for aircraft engines. - Power generation for gas turbine power plants. - Marine propulsion systems for ships.

Problems Solved: - Control deformation of airfoil components. - Improve efficiency and performance of gas turbine engines. - Enhance safety and reliability of engine operation.

Benefits: - Increased durability and lifespan of airfoil components. - Enhanced control over deformation under varying operating conditions. - Improved overall performance and efficiency of gas turbine engines.

Commercial Applications: Title: "Advanced Airfoil Technology for Gas Turbine Engines" This technology can be utilized in commercial aircraft engines, power generation plants, and marine propulsion systems. It offers improved performance, efficiency, and safety, making it attractive for companies in the aerospace, energy, and maritime industries.

Questions about the technology: 1. How does the crush initiator on the stiffener control deformation in the airfoil? 2. What are the specific advantages of using this technology in gas turbine engines?

Original Abstract Submitted

a gas turbine engine includes a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine centerline. an airfoil is located in one of the fan section, the compressor section, or the turbine section. the airfoil defines an interior and extends between a leading edge and a trailing edge defining a chord-wise direction, and extending between a root and a tip defining a span-wise direction. at least one stiffener is located within the interior, having a deformation threshold, and including at least one crush initiator formed on the at least one stiffener. the crush initiator determines deformation geometry of the at least one stiffener in response to a force acting on the at least one stiffener exceeding the deformation threshold.