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US 11,885,233 B2Granted
Turbine engine with airfoil having high acceleration and low blade turning
AssigneesGeneral Electric Company, GE Avio S.r.l.
InventorsErnesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
Life of this patent
Estimating the term…
Abstract
A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
Claims20
An airfoil assembly comprising:
- at least two airfoils carried by a rotor and configured to rotate about a rotational axis, the at least two airfoils being circumferentially spaced from each other, with respect to the rotational axis, to define a pitch (P) therebetween, each airfoil of the at least two airfoils comprising:
- an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip;
- a mean camber line extending between the leading edge and the trailing edge and intersecting the leading edge to define a leading edge intersection, and intersecting the trailing edge to define a trailing edge intersection;
- an inlet angle, βin, in degrees, defined by an included angle between a line parallel to the mean camber line at the leading edge intersection and the rotational axis;
- and
- an outlet angle, βout, in degrees, defined by an included angle between a line parallel to the mean camber line at the trailing edge intersection and the rotational axis;
- an axial chord length (Cax) extending between the leading edge and the trailing edge in an axial direction with respect to the rotational axis;
- a blade turning (BT) of less than 100 degrees along at least 30% of a span of the airfoil, wherein the blade turning (BT) is determined by:
- BT
- =
- ❘
- "\[LeftBracketingBar]"
- β
- out
- ❘
- "\[RightBracketingBar]"
- +
- β
- i
-
- n
- *
- β
- out
- ❘
- "\[LeftBracketingBar]"
- β
- out
- ❘
- "\[RightBracketingBar]"
- and
- an airfoil solidity (Sl) of the at least two airfoils is determined by:
- c
- a
-
- x
- P
- ;
- wherein the airfoil solidity (Sl) is greater than or equal to 0.6 and less than or equal to 1.2 (0.6≤Sl≤1.2);
- and
- wherein βin is constant along the span from the root to the tip, or βout is constant along the span from the root to the tip.
38 more elements
An airfoil operably coupled to a rotor and configured to rotate about a rotational axis, the airfoil comprising:
- an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip to define a span (S);
- an axial chord length (Cax) extending between the leading edge and the trailing edge in an axial direction with respect to the rotational axis;
- and
- an aspect ratio (AR) of the airfoil is determined by:
- C
- ax
- S
- ;
- wherein the aspect ratio (AR) is greater than or equal to 2 and less than or equal to 6 (2<AR<6);
- and
- wherein βin is constant along the span from the root to the tip, or βout is constant along the span from the root to the tip.
8 more elements
An airfoil operably coupled to a rotor and assembly, the airfoil being rotatable about a rotational axis, the airfoil comprising:
- an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip;
- a mean camber line extending between the leading edge and the trailing edge and intersecting the leading edge to define a leading edge intersection, and intersecting the trailing edge to define a trailing edge intersection;
- an inlet angle, βin, in degrees, defined by an included angle between a line parallel to the mean camber line at the leading edge intersection and the rotational axis;
- an outlet angle, βout, in degrees, defined by an included angle between a line parallel to the mean camber line at the trailing edge intersection and the rotational axis;
- and
- a contraction ratio (CR) of greater than 0.55 along at least 80% of a span of the airfoil, wherein the contraction ratio (CR) is determined by
- CR
- =
- 1
- -
- (
- cos
-
- (
- β
- out
- )
- cos
-
- (
- β
- i
-
- n
- )
- )
- .
24 more elements
An airfoil operably coupled to a rotor assembly, the airfoil comprising:
- at least two airfoils carried by a rotor and configured to rotate about a rotational axis, the at least two airfoils being circumferentially spaced from each other, with respect to the rotational axis, to define a pitch (P) therebetween, each airfoil of the at least two airfoils comprising:
- an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip;
- a mean camber line extending between the leading edge and the trailing edge and intersecting the leading edge to define a leading edge intersection, and intersecting the trailing edge to define a trailing edge intersection;
- an inlet angle, βin, in degrees, defined by an included angle between a line parallel to the mean camber line at the leading edge intersection and the rotational axis;
- an outlet angle, βout, in degrees, defined by an included angle between a line parallel to the mean camber line at the trailing edge intersection and the rotational axis;
- an axial chord length (Cax) extending between the leading edge and the trailing edge in an axial direction with respect to the rotational axis;
- a contraction ratio (CR) is greater than 0.55 along at least 80% of the span, wherein the contraction ratio (CR) is determined by:
- CR
- =
- 1
- -
- (
- cos
-
- (
- β
- out
- )
- cos
-
- (
- β
- i
-
- n
- )
- )
- ;
- a blade turning (BT) of less than 100 degrees alone at least 30% of the span, wherein the blade turning (BT) is determined by:
- BT
- =
- ❘
- "\[LeftBracketingBar]"
- β
- out
- ❘
- "\[RightBracketingBar]"
- +
- β
- i
-
- n
- *
- β
- out
- ❘
- "\[LeftBracketingBar]"
- β
- out
- ❘
- "\[RightBracketingBar]"
- an airfoil solidity (Sl) of the at least two airfoils is determined by:
- C
- ax
- P
- ,
- with the airfoil solidity (Sl) being greater than or equal to 0.6 and less than or equal to 1.2 (0.6<Sl<1.2);
- and
- an aspect ratio (AR) of the airfoil is determined by:
- C
- ax
- S
- ,
- with the aspect ratio (AR) being greater than or equal to 2 and less than or equal to 6 (2<AR<6).
61 more elements
Dependencies are inferred from the claim text.