Gas turbine engine with bow wave mitigation
A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section. The turbine section includes a band having an upstream end and a downstream end. The band extends between the upstream end and the downstream end, and the band at least partially defines the working gas flow path. A plurality of airfoils extend into the working gas flow path from the band. Each airfoil of the plurality of airfoils includes a leading edge, a trailing edge, a first side, and a second side opposite the first side. Each of the plurality of airfoils is substantially symmetric across an airfoil centerline extending through a center of each of the plurality of airfoils. The band defines a valley portion adjacent the leading edge of each of the plurality of airfoils and a pair of hill portions on opposing sides of the valley portion.
1. A gas turbine engine, comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section collectively defining at least in part a working gas flow path, the turbine section comprising:
a band comprising an upstream end and a downstream end, the band extending between the upstream end and the downstream end, the band at least partially defining the working gas flow path, and
a plurality of airfoils extending into the working gas flow path from the band, wherein each airfoil of the plurality of airfoils includes a leading edge, a trailing edge, a first side extending between the leading edge and the trailing edge, and a second side opposite the first side and extending between the leading edge and the trailing edge, and wherein each of the plurality of airfoils is symmetric across an airfoil centerline extending through a center of each of the plurality of airfoils;
wherein the upstream end of the band defines a valley portion adjacent the leading edge of each of the plurality of airfoils and a pair of hill portions on opposing sides of the valley portion.
2. The gas turbine engine of claim 1 , wherein:
the plurality of airfoils define an airfoil pitch (P) extending between the airfoil centerline of adjacent ones of the plurality of airfoils;
each hill of the pair of hill portions defines a normalized hill width (HW n ) defined by a hill width (HW) of each hill of the pair of hill portions and the airfoil pitch (P) of the plurality of airfoils;
the normalized hill width (HW n ) is equal to HW/P; and
the normalized hill width (HW n ) is greater than or equal to 0.1 and less than or equal to 0.4.
3. The gas turbine engine of claim 2 , wherein the normalized hill width (HW n ) is greater than or equal to 0.2 and less than or equal to 0.35.
4. The gas turbine engine of claim 1 , wherein:
each hill of the pair of hill portions defines a normalized hill height (HH n ) defined by a hill height (H hill ) of each hill of the pair of hill portions and an airfoil height (H airfoil ) of the plurality of airfoils measured at the leading edge;
the normalized hill height (HH n ) is equal to
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and
the normalized hill height (HH n ) is greater than 0.005 and less than 0.1.
5. The gas turbine engine of claim 1 , wherein:
the valley portion defines a normalized valley depth (VD n ) defined by a valley depth (D) of the valley portion and an airfoil height (H airfoil ) of the plurality of airfoils at the leading edge;
the normalized valley depth (VD n ) is equal to
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and
the normalized valley depth (VD n ) is greater than or equal to 0 and less than or equal to 0.1.
6. The gas turbine engine of claim 1 , wherein:
the plurality of airfoils define an airfoil pitch (P) extending between the airfoil centerline of adjacent ones of the plurality of airfoils;
the valley portion defines a normalized valley width (VW n ) defined by a valley width (VW) of the valley portion and the airfoil pitch (P) of the plurality of airfoils;
the normalized valley width (VW n ) is equal to VW/P; and
the normalized valley width (VW n ) is greater than or equal to 0 and less than or equal to 0.2.
7. The gas turbine engine of claim 1 , wherein:
the leading edge of the plurality of airfoils define a leading edge diameter; and
the valley portion and the pair of hill portions are disposed upstream of an aft end of the leading edge diameter.
8. The gas turbine engine of claim 1 , wherein the valley portion and the pair of hill portions extend into the upstream end of the band.
9. The gas turbine engine of claim 1 , wherein the plurality of airfoils comprise a plurality of stator vanes disposed between a high-pressure turbine and a low-pressure turbine of the turbine section.
10. The gas turbine engine of claim 1 , wherein the plurality of airfoils comprise a plurality of stator vanes extending between a turbine center frame inner band and a turbine center frame outer band of a turbine center frame of the turbine section.
11. The gas turbine engine of claim 1 , wherein the plurality of airfoils comprise a plurality of stator vanes extending between a turbine rear frame inner band and a turbine rear frame outer band of a turbine rear frame of the turbine section.
12. The gas turbine engine of claim 1 , wherein a mean contour line is defined between the valley portion and the pair of hill portions, wherein the valley portion extends below the mean contour line and defines a concave curve, and wherein the pair of hill portions extend above the mean contour line and define a convex curve.
13. The gas turbine engine of claim 12 , wherein:
the plurality of airfoils includes an airfoil height measured at the leading edge extending from the band; and
a hill peak of each of the pair of hill portions extends above the mean contour line to define a hill height, wherein the hill height divided by the airfoil height is greater than 0.005 and less than 0.1.
14. The gas turbine engine of claim 12 , wherein:
the plurality of airfoils includes an airfoil height measured at the leading edge extending from the band; and
a base of the valley portion extends below the mean contour line to define a valley depth, wherein the valley depth divided by the airfoil height is greater than or equal to 0 and less than or equal to 0.1.
15. The gas turbine engine of claim 1 , wherein the plurality of airfoils comprise a plurality of stator vanes disposed in a low-pressure turbine of the turbine section.
16. The gas turbine engine of claim 1 , wherein a first set of the pair of hill portions adjacent a first one of the plurality of airfoils is spaced from a second set of the pair of hill portions adjacent a second one of the plurality of airfoils, and wherein the second one of the plurality of airfoils is adjacent the first one of the plurality of airfoils.
17. The gas turbine engine of claim 1 , wherein:
the band comprises an inner band extending between the upstream end and the downstream end and an outer band spaced from the inner band in a radial direction and extending between the upstream end and the downstream end; and
the upstream end of one or both of the inner band and the outer band defines the valley portion and the pair of hill portions.
18. The gas turbine engine of claim 1 , wherein the upstream end of the band comprises an upstream end of a turbine center frame aft of a high pressure turbine of the turbine section.
19. The gas turbine engine of claim 1 , wherein the upstream end of the band comprises an upstream end of a turbine rear frame aft of a low pressure turbine of the turbine section.
20. The gas turbine engine of claim 1 , wherein:
each hill of the pair of hill portions defines a hill peak at a maximum height of each hill of the pair of hill portions;
the valley portion defines a valley base at a maximum depth of the valley portion; and
the hill peak and the valley base are upstream of the leading edge of the plurality of airfoils.