Pressure recovery axial-compressor blading
AssigneeROLLS-ROYCE plc
InventorBronwyn Power
Life of this patent
Estimating the term…
Abstract
In accordance with some embodiments of the present disclosure, a pressure recovery axial compressor blade is provided. The blade may comprise a high pressure surface and a low pressure surface connected at a leading edge and a trailing edge of the blade. Both the high and low pressure surfaces extend span wise from a first end to a second end. At least one of the high and low pressure surfaces has a finite discontinuity in curvature at an intermediate position along the chord of the blade.
Claims20
A blade comprising:
- a high pressure surface, and a low pressure surface connected at a leading edge and trailing edge of the blade;
- the high pressure and low pressure surfaces extending span wise from a first end to a second end;
- the low pressure surface having a discontinuity in the chord-wise curvature of an intermediate portion of the low pressure surface between the blade leading edge and blade trailing edge;
- and the high pressure and low pressure surfaces form an uninterrupted surface between the first and second ends.
In a gas turbine having a turbomachine with plurality of blades extending radially between a hub and a casing which operates on a gas stream, each of the blades having a high pressure surface and a low pressure surface between a leading edge and a trailing edge, the high pressure and low pressure surfaces being uninterrupted, the low pressure surface having a discontinuity in curvature, a method of pressure recovery for each blade comprising:
- accelerating the gas stream to a subsonic velocity over the low pressure surface,
- maintaining the subsonic velocity of the gas stream approximately constant across the low pressure surface on a front half chord of the blade;
- introducing a discontinuity in a curvature of the low pressure surface;
- and,
- rapidly reducing the velocity of the gas stream proximate the discontinuity, thereby recovering pressure.
A turbine compressor blade comprising:
- a solid interior bounded by a high pressure surface, a low pressure surface, a leading edge, a trailing edge, a first end, and a second end, wherein the high and low pressure surfaces are connected to each other at the leading and trailing edges and both extend from the first end to the second end,
- wherein at least one of the high pressure surface and the low pressure surface has a discontinuity in curvature at an intermediate position along a chord of the blade.
Dependencies are inferred from the claim text.