Compressor casing structure
AssigneeMTU Aero Engines AG
InventorJuergen Schmuecker
Life of this patent
Estimating the term…
Abstract
A compressor casing structure in the region of a rotor blade ring through which there is an axial flow, having a multiplicity of axial grooves which extend from a first radial plane upstream of the blade-tip inlet edges into a second radial plane between the blade-tip inlet edges and the blade-tip outlet edges and have groove cross sections with parallel side walls. The center axes of the groove cross sections have, at the upstream groove ends, from the opening to the groove base, an angle of inclination with a circumferential component counter to the direction of movement of the blade. The center axes of the groove cross sections have, at the downstream groove ends, an angle of inclination with a circumferential component in the direction of movement of the blade.
Claims16
A compressor casing structure in a region of a rotor blade ring through which there is an axial flow, comprising a multiplicity of grooves which are distributed uniformly over a circumference of the casing, are open towards blade tips of the rotor blade ring, run at least approximately axially, extend axially from a first radial plane upstream of blade-tip inlet edges into a second radial plane between the blade-tip inlet edges and blade-tip outlet edges and have, in each case in the radial section, groove cross sections with side walls which are straight and parallel over a large part of their depth, wherein the center axes of the groove cross sections have at upstream groove ends, from an opening to a groove base, an angle of inclination with respect to a radial direction with a circumferential component counter to a direction of movement of the blade tips, and wherein the center axes of the groove cross sections have at downstream groove ends, from the opening to the groove base, an angle of inclination with respect to the radial direction with a circumferential component in the direction of movement of the blade tips, wherein the angle of inclination of the center axes of the groove cross sections changes continuously in a swirling twisting manner between the upstream and the downstream groove ends, and wherein sectional lines of the center axes of the groove cross sections with an outer casing-end annular space contour are at least approximately axial straight elements so that the openings of the grooves extend axially in the same way.
A compressor casing structure in a region of a rotor blade ring having blades, comprising:
- a plurality of grooves distributed uniformly over a circumference of the casing, wherein each groove has an opening, a base, and a center axis;
- wherein the center axis of one of the grooves at an upstream groove end has an angle of inclination counter to a direction of movement of a tip of the blades;
- and
- wherein the center axis of the one of the grooves at a downstream groove end has an angle of inclination in the direction of movement of the tip of the blades.
A method for recirculating air in a compressor casing structure, comprising the steps of:
- flowing air at a downstream location in a flow channel in the compressor casing structure into a groove;
- flowing the air in the groove from the downstream location to an upstream location;
- and
- flowing the air out of the groove into the flow channel at an upstream location;
- wherein the groove has an angle of inclination at a downstream groove end in a direction of movement of a tip of a blade housed in the compressor casing structure and wherein the groove has an angle of inclination at an upstream groove end counter to the direction of movement.
Dependencies are inferred from the claim text.