20240026796. GUIDE VANES IN A GAS TURBINE ENGINE simplified abstract (Siemens Energy Global GmbH & Co. KG.)

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GUIDE VANES IN A GAS TURBINE ENGINE

Organization Name

Siemens Energy Global GmbH & Co. KG.

Inventor(s)

Bengt Johansson of Linköping (SE)

Almir Ajkunic of Norrköping (SE)

Ranjith Kumar Arinipalli of Finspång (SE)

Antonio Pesare of Norrköping (SE)

GUIDE VANES IN A GAS TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240026796 titled 'GUIDE VANES IN A GAS TURBINE ENGINE

Simplified Explanation

The abstract describes a guide vane in a gas turbine engine that consists of an inner platform, an outer platform, and an airfoil between them. The side surfaces of the inner and outer platforms form three seal slots, one of which has a rounded corner. The guide vane also includes tubulator ribs and pin fins in the airfoil interior, with the pin fins located near the trailing edge. The inner platform has film cooling holes arranged in a fan shape on its outer surface, while both the inner and outer platforms have impingement cooling ribs on their respective surfaces. The inner platform extends further upstream in the flow direction compared to the outer platform.

  • The guide vane in a gas turbine engine has an inner platform, an outer platform, and an airfoil in between.
  • The inner and outer platforms form seal slots, one of which has a rounded corner.
  • Tubulator ribs and pin fins are present in the airfoil interior, with the pin fins located near the trailing edge.
  • The inner platform has film cooling holes arranged in a fan shape on its outer surface.
  • Both the inner and outer platforms have impingement cooling ribs on their respective surfaces.
  • The inner platform extends further upstream in the flow direction compared to the outer platform.

Potential applications of this technology:

  • Gas turbine engines in aviation and power generation industries.
  • Enhancing the performance and efficiency of gas turbine engines.
  • Improving the cooling capabilities of guide vanes in gas turbine engines.

Problems solved by this technology:

  • Reducing leakage and improving sealing efficiency in guide vanes.
  • Enhancing cooling effectiveness in the airfoil and platform regions.
  • Minimizing heat-related damage and improving overall durability.

Benefits of this technology:

  • Increased efficiency and performance of gas turbine engines.
  • Improved reliability and lifespan of guide vanes.
  • Enhanced cooling capabilities for better engine operation.
  • Potential for reduced maintenance and repair costs.


Original Abstract Submitted

a guide vane in a gas turbine engine includes an inner platform, an outer platform, and an airfoil extending therebetween. side surfaces of the inner platform and outer platform between an adjacent guide vane define a first seal slot, a second seal slot, and a third seal slot forming a closed loop having three corners. at least one of the corners is rounded. the guide vane includes tubulator ribs and pin fins disposed in an airfoil interior. the pin fins are disposed in a region of the trailing edge. the inner platform defines film cooling holes disposed at an outer surface facing the airfoil. the film cooling holes are arranged in a fan shape. an inner surface of the inner platform and an outer surface of the outer platform include impingement cooling ribs. the inner platform protrudes further towards upstream in a flow direction than the outer platform.

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