Fan exit guide vane platform contouring

Patent metadata

Field	Value
Publication number	US-10196897-B2
Application number	US-201414774190-A
Country	US
Kind code	B2
Filing date	Mar 13, 2014
Priority date	Mar 15, 2013
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

A turbofan engine includes a fan section with a plurality of fan blades rotatable about an engine axis generating an airflow, a bypass passage through which the airflow passes, and a fan exit guide vane. The fan exit guide vane assembly includes a plurality of airfoils disposed between an inner platform wall and an outer platform wall. At least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent airfoils. The contoured surface includes at least one concave region and at least one convex region. A method of reducing secondary flow structures in bypass air flow with the turbofan is also disclosed.

First claim

What is claimed is:

1. A turbofan engine comprising:
a fan section including a plurality of fan blades rotatable about an engine axis generating an airflow;
a bypass passage through which the airflow passes; and
a fan exit guide vane assembly including a plurality of airfoils disposed between an inner platform wall and an outer platform wall, wherein at least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent ones of the plurality of airfoils, and wherein the contoured surface includes at least one concave region and at least one convex region, wherein at least one of the at least one convex region and the at least one concave regions comprise a subregion with a concavity or convexity different from that of the convex or concave region.

2. The turbofan engine as recited in claim 1 , wherein one of the inner and outer platform walls has an axisymmetric cross-section at a leading edge and a trailing edge of a plane defined by the adjacent ones of the plurality of airfoils, and the leading and trailing edges of the adjacent ones of the plurality of airfoils bound an axial extent of the contoured surface.

3. The turbofan engine as recited in claim 1 , wherein the at least one convex region includes first and second convex regions adjacent to first and second airfoils of the plurality of airfoils, respectively.

4. The turbofan engine as recited in claim 3 , wherein the first and second convex regions extend axially from near a first midchord of the first airfoil and a second midchord of the second airfoil to near trailing edges of the first and second airfoils, respectively.

5. The turbofan engine as recited in claim 1 , wherein the contoured surface transitions gradually from the at least one convex region to the at least one concave region.

6. A turbofan engine comprising:
a fan section including a plurality of fan blades rotatable about an engine axis generating an airflow;
a bypass passage through which the airflow passes; and
a fan exit guide vane assembly including a plurality of airfoils disposed between an inner platform wall and an outer platform wall, wherein at least one of the inner platform wall and the outer platform wall includes a contoured surface between adjacent ones of the plurality of airfoils, and wherein the contoured surface includes at least one concave region and at least one convex region, wherein the at least one convex region includes first and second convex regions adjacent to first and second airfoils of the plurality of airfoils, respectively, wherein the first and second convex regions extend axially from near a first midchord of the first airfoil and a second midchord of the second airfoil to near trailing edges of the first and second airfoils, respectively, wherein the at least one concave region includes a first concave region having first and second prongs.

7. The turbofan engine as recited in claim 6 , wherein the at least one convex region includes a third convex region between the first and second prongs of the first concave region.

8. The turbofan engine as recited in claim 6 , wherein the first and second prongs are oriented towards trailing edges of the adjacent ones of the plurality of airfoils.

9. The turbofan engine as recited in claim 8 further comprising a second concave region adjacent to a pressure side of one of the first and second airfoils.

10. The turbofan engine as recited in claim 9 , further comprising a fourth convex region between the first and second concave regions.

Assignees

• United Technologies Corp

Inventors

• Thomas Flavien L

Classifications

• F05D2250/712

  concave · CPC title

• F05D2250/711

  convex · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F02K3/06

  with front fan · CPC title

• F01D5/143 Primary

  Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour · CPC title