US 9,920,640 B2Granted

Extruded profile for manufacturing a blade of an outlet guide vane

AssigneeMTU Aero Engines AG

InventorMartin Hoeger

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Abstract

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

Claims23

Dependent claims

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine, the extruded profile comprising:

a cross-sectional area having an axial length LAX and a thickness D/LAX relative to axial length LAX, along axial length LAX thereof, the cross-sectional area having the following mutually adjoining regions:
an at least nearly axisymmetric leading edge region;
a first transition region having a relative thickness D/LAX varying along the first transition region;
a first constant region having a relative thickness D/LAX at least substantially constant along the first constant region, the first constant region, relative to a leading edge of the extruded profile, beginning at the closest at 10% LAX and ends at the furthest at 50% LAX;
a second transition region having a relative thickness D/LAX varying along the second transition region, the second transition region, relative to the leading edge, beginning at the closest at 30% LAX and ending at the furthest at 90% LAX;
a second constant region having a relative thickness D/LAX at least substantially constant along the second constant region, the second constant region having an axial length X of 40% LAX at most;
and
an at least nearly axisymmetric trailing edge region, wherein the first constant region has a relative thickness D/LAX of between 3% and 6% LAX or, relative to the leading edge of the extruded profile, the first constant region extends within the range of approximately 20% to 40% LAX, and wherein the first constant region relative thickness D/LAX is approximately 4% LAX.

5 more elements

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine, the extruded profile comprising:

a cross-sectional area having an axial length LAX and a thickness D/LAX relative to axial length LAX, along axial length LAX thereof, the cross-sectional area having the following mutually adjoining regions:
an at least nearly axisymmetric leading edge region;
a first transition region having a relative thickness D/LAX varying along the first transition region;
a first constant region having a relative thickness D/LAX at least substantially constant along the first constant region, the first constant region, relative to a leading edge of the extruded profile, beginning at the closest at 10% LAX and ends at the furthest at 50% LAX;
a second transition region having a relative thickness D/LAX varying along the second transition region, the second transition region, relative to the leading edge, beginning at the closest at 30% LAX and ending at the furthest at 90% LAX;
a second constant region having a relative thickness D/LAX at least substantially constant along the second constant region, the second constant region having an axial length X of 40% LAX at most;
and
an at least nearly axisymmetric trailing edge region, and wherein the extruded profile further comprises a suction side having a basic shape that is at least predominantly plane along the axial length LAX.

5 more elements

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine, the extruded profile comprising:

a cross-sectional area having an axial length LAX and a thickness D/LAX relative to axial length LAX, along axial length LAX thereof, the cross-sectional area having the following mutually adjoining regions:
an at least nearly axisymmetric leading edge region;
a first transition region having a relative thickness D/LAX varying along the first transition region;
a first constant region having a relative thickness D/LAX at least substantially constant along the first constant region, the first constant region, relative to a leading edge of the extruded profile, beginning at the closest at 10% LAX and ends at the furthest at 50% LAX;
a second transition region having a relative thickness D/LAX varying along the second transition region, the second transition region, relative to the leading edge, beginning at the closest at 30% LAX and ending at the furthest at 90% LAX;
a second constant region having a relative thickness D/LAX at least substantially constant along the second constant region, the second constant region having an axial length X of 40% LAX at most;
and
an at least nearly axisymmetric trailing edge region, and wherein the extruded profile further comprises a pressure side having a basic form curved in an approximate S-shape, at least in the area of the second transition region.

5 more elements

A method for manufacturing a blade of an outlet guide vane of a turbine engine comprising:

preparing an extruded profile including a cross-sectional area having an axial length LAX and a thickness D/LAX relative to axial length LAX, along axial length LAX thereof, the cross-sectional area having the following mutually adjoining regions:
an at least nearly axisymmetric leading edge region,
a first transition region having a relative thickness D/LAX varying along the first transition region;
a first constant region having a relative thickness D/LAX at least substantially constant along the first constant region, the first constant region, relative to a leading edge of the extruded profile, beginning at the closest at 10% LAX and ends at the furthest at 50% LAX,
a second transition region having a relative thickness D/LAX varying along the second transition region, the second transition region, relative to the leading edge, beginning at the closest at 30% LAX and ending at the furthest at 90% LAX;
a second constant region having a relative thickness D/LAX at least substantially constant along the second constant region, the second constant region having an axial length X of 40% LAX at most, and
an at least nearly axisymmetric trailing edge region;
and
producing blades from the extruded profile using a manufacturing method including reshaping and separating processes;
wherein the reshaping includes reshaping the extruded profile at least in the leading edge region and the separating includes separating the extruded profile, at least in one region downstream of the first transition region.

7 more elements

Dependencies are inferred from the claim text.