Extruded profile for manufacturing a blade of an outlet guide vane

Patent metadata

Field	Value
Publication number	US-9920640-B2
Application number	US-201514595094-A
Country	US
Kind code	B2
Filing date	Jan 12, 2015
Priority date	Jan 16, 2014
Publication date	Mar 20, 2018
Grant date	Mar 20, 2018

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.

First claim

What is claimed is:

1. 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.

2. The extruded profile as recited in claim 1 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 1% and 5% LAX.

3. The extruded profile as recited in claim 2 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 2% and 4% LAX.

4. The extruded profile as recited in claim 1 wherein the first transition region has an axial length X of 20% LAX at most or, relative to the leading edge of the extruded profile, the second transition region ends at the furthest at approximately 80% LAX.

5. The extruded profile as recited in claim 1 wherein the profile is metal or a metal alloy or is produced by extrusion.

6. The extruded profile as recited in claim 5 wherein the profile is made of a high-temperature resistant metal alloy.

7. A blade of an outlet guide vane of a turbine engine obtainable or obtained from the extruded profile as recited in claim 1 .

8. An outlet guide vane for a turbine engine comprising at least one blade as recited in claim 7 .

9. A turbine engine comprising at least one outlet guide vane as recited in claim 8 .

10. An aircraft engine comprising the turbine engine as recited in claim 9 .

11. The turbine engine as recited in claim 9 wherein the outlet guide vane is configured in the area of a turbine outlet of the turbine engine.

12. The outlet guide vane for a turbine engine comprising at least two blades as recited in claim 7 , the at least two blades having different axial lengths LAX.

13. 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.

14. The extruded profile as recited in claim 13 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 1% and 5% LAX.

15. The extruded profile as recited in claim 13 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 2% and 4% LAX.

16. The extruded profile as recited in claim 13 wherein the first transition region has an axial length X of 20% LAX at most or, relative to the leading edge of the extruded profile, the second transition region ends at the furthest at approximately 80% LAX.

17. 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.

18. The extruded profile as recited in claim 17 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 1% and 5% LAX.

19. The extruded profile as recited in claim 17 wherein the leading edge region or the trailing edge region is configured to be at least substantially circular segment shaped with a circular segment diameter of between 2% and 4% LAX.

20. The extruded profile as recited in claim 17 wherein the first transition region has an axial length X of 20% LAX at most or, relative to the leading edge of the extruded profile, the second transition region ends at the f

Assignees

• MTU Aero Engines AG

Inventors

• Hoeger Martin

Classifications

• F05D2250/70

  Shape · CPC title

• F05D2220/3215

  the last stage of the turbine · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2250/73

  asymmetric · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title