20240011401. TURBINE BLADE WITH MODAL RESPONSE ADAPTED TIP SHROUD simplified abstract (Power Systems Mfg., LLC)

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TURBINE BLADE WITH MODAL RESPONSE ADAPTED TIP SHROUD

Organization Name

Power Systems Mfg., LLC

Inventor(s)

Douglas James Dietrich of West Palm Beach FL (US)

Alexander Vasili Rozendaal of Palm Beach Garden FL (US)

Stephen Fiebiger of Jupiter FL (US)

Alex Torkaman of Port St Lucie FL (US)

TURBINE BLADE WITH MODAL RESPONSE ADAPTED TIP SHROUD - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240011401 titled 'TURBINE BLADE WITH MODAL RESPONSE ADAPTED TIP SHROUD

Simplified Explanation

The abstract describes a gas turbine blade for a gas turbine engine. The blade includes an attachment, a blade neck portion, a platform, an airfoil, and a shroud. The blade neck portion extends radially outward from the attachment, and the platform is attached to the blade neck portion opposite the attachment. The airfoil extends radially outward from the platform and includes a leading edge, a trailing edge, and an axial chord defined between them. The shroud is attached to an end of the airfoil and includes an upper surface and a modal response tuning component attached to the upper surface of the shroud. The modal response tuning component is offset from the mid-chord point by a predetermined distance to move the modal response of the gas turbine blade outside of the operating speed range.

  • Gas turbine blade for a gas turbine engine
  • Includes attachment, blade neck portion, platform, airfoil, and shroud
  • Blade neck portion extends radially outward from the attachment
  • Platform is attached to the blade neck portion opposite the attachment
  • Airfoil extends radially outward from the platform
  • Airfoil has a leading edge, a trailing edge, and an axial chord defined between them
  • Shroud is attached to an end of the airfoil
  • Shroud includes an upper surface
  • Modal response tuning component is attached to the upper surface of the shroud
  • Modal response tuning component is offset from the mid-chord point by a predetermined distance
  • Offset moves the modal response of the gas turbine blade outside of the operating speed range

Potential applications of this technology:

  • Gas turbine engines in various industries such as aviation, power generation, and marine propulsion

Problems solved by this technology:

  • Enhances the performance and efficiency of gas turbine engines
  • Reduces the risk of blade vibrations and failures within the operating speed range

Benefits of this technology:

  • Improved reliability and durability of gas turbine blades
  • Increased operational efficiency and power output of gas turbine engines
  • Reduced maintenance and downtime due to blade failures


Original Abstract Submitted

a gas turbine blade for a gas turbine engine includes an attachment, a blade neck portion, a platform, an airfoil, and a shroud. the gas turbine engine has an operating speed range. the blade neck portion extends radially outward from the attachment. the platform is attached to the blade neck portion opposite the attachment. the airfoil extends radially outward from the platform. the airfoil includes a leading edge, a trailing edge, and an axial chord defined between the leading and trailing edges. the axial chord defines a mid-chord point. the shroud is attached to an end of the airfoil. the shroud includes an upper surface and a modal response tuning component attached to the upper surface of the shroud. the modal response tuning component is offset from the mid-chord point a predetermined distance to move modal response of the gas turbine blade outside of the operating speed range.

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