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Turbomachinery rotor blade

a technology of rotor blades and turbines, applied in the direction of blade accessories, machines/engines, mechanical apparatus, etc., can solve the problems of more deleterious effects, and achieve the effect of improving aerodynamic performan

Active Publication Date: 2019-08-20
WABTEC UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The blade design reduces stress and maintains aerodynamic performance by minimizing gas stream disruption and extending the contact area with the lacing wire, improving efficiency and fatigue life.

Problems solved by technology

Further, thickening on the suction side of the blade, where air speeds are higher, tends to have a more deleterious effect than thickening on the pressure side of the blade.

Method used

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  • Turbomachinery rotor blade
  • Turbomachinery rotor blade
  • Turbomachinery rotor blade

Examples

Experimental program
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Effect test

Embodiment Construction

[0029]FIG. 2 shows schematically (a) a row of blades for an axial flow turbocharger turbine rotor viewed from the pressure side and (b) a close-up view of one of the blades viewed from the suction side. Each blade 11 has an aerofoil body 13 with a pressure surface 15 and a suction surface 17. A hole 19 penetrates through the aerofoil body from the suction surface to the pressure surface such that a lacing wire can be passed through the hole to link the blade to neighbouring blades.

[0030]The blade 11 has a protrusion 21 from the pressure surface 15 and another similar protrusion 21 from the suction surface 17. The protrusions are local thickenings of the aerofoil body and extend in a downstream direction from the downstream side of the hole. Advantageously, these local thickenings increase the contact area between the blade and a wire inserted through the hole 19, reducing the stresses produced in the blade by the inertial load of the wire. Although not shown here, another option is ...

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PUM

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Abstract

A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protrusion from the suction or pressure surface. The protrusion extends in a downstream direction from a downstream side of the hole and / or extends in an upstream direction from an upstream side of the hole, thereby disturbing the suction or pressure surface to locally thicken the aerofoil body adjacent the hole. The maximum radial extent of the protrusion in the radially outward direction of the blade is radially coterminous with the outboard side of the hole, and the maximum radial extent of the protrusion in the radially inward direction of the blade is radially coterminous with the inboard side of the hole.

Description

FIELD OF THE INVENTION[0001]The present invention relates to a turbomachinery rotor blade.BACKGROUND[0002]Turbines operating in highly pulsating gas flows may need additional damping / stiffness in order to ensure their survival. This additional damping / stiffness can be provided by inserting a lacing wire through holes in the turbine blades to tie them together and support them during operation.[0003]However, during operation the lacing wire applies an inertial load which produces stresses in the blades. To prevent these stresses from becoming excessive, a boss may be added around the hole in each blade.[0004]The boss is a local thickening of the aerofoil section of the blade, which reduces the stresses produced in the blade by the inertial load of the wire. For example, FIG. 1 shows neighbouring industrial turbocharger turbine blades 1 with a lacing wire 3 inserted through holes 5 in the aerofoil bodies 7 of the blades. A boss 9 surrounds each hole and supports the wire.[0005]Althoug...

Claims

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Application Information

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Patent Type & Authority Patents(United States)
IPC IPC(8): F01D5/24
CPCF01D5/24F05D2220/40
Inventor THOMAS, NEIL RYAN
Owner WABTEC UK LTD