Gas turbine engine rotor blade geometry and method for selecting same
An aircraft propulsion system includes a bladed rotor configured for rotation about a rotational axis. A rotor blade of the bladed rotor of rotor blades includes a blade body. The blade body has a blade span extending between and to a base end and a tip end. The blade body has a blade chord extending between and to a leading edge and a trailing edge. The blade body forms a pressure side surface and a suction side surface. The blade body forms a recess at the pressure side surface. The recess includes a recess surface portion forming a portion of the pressure side surface. The recess surface portion has a recess height. The recess height is greater than or equal to a Y-value of 0.025 for a normalized two-dimensional curve of a surface profile of the recess surface portion taken along a Y-Z plane orthogonal to the rotational axis for a recess span.
1 . A method comprising:
observing a Y-Z plane orthogonal to a rotational axis of a blade body of a rotor blade, a Z-direction of the Y-Z plane extends in a span direction of the blade body, a Y-direction of the Y-Z plane extends orthogonal to the Z-direction;
intersecting the Y-Z plane with a recess forming a portion of a pressure side surface of the blade body to obtain a two-dimensional curve of a surface profile of the pressure side surface;
extracting and normalizing Y-coordinates and Z-coordinates of the two-dimensional curve to determine a normalized two-dimensional curve of the surface profile of the pressure side surface;
determining a straight-line equation for a straight line intersecting the normalized two-dimensional curve at a minimum span position and a maximum span position for the recess; and
selecting a recess height of the recess such that the recess height is greater than or equal to a Y-value of 0.025 and less than or equal to the Y-value of 0.1, and the recess height is a maximum height measured in the Y-direction between the normalized two-dimensional curve and the straight line.
2 . The method of claim 1 , wherein selecting the recess height further includes selecting the recess height within a recess axial chord of the recess extending between and to a minimum axial chord position and a maximum axial chord position, the minimum axial chord position is greater than or equal to 50 percent of a blade axial chord of the blade body and the maximum chord position is less than or equal to 80 percent of the blade axial chord.
3 . The method of claim 2 , wherein selecting the recess height further includes selecting the recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1 for a plurality of axial positions, relative to the rotational axis, between and to the minimum axial chord position and the maximum axial chord position.
4 . The method of claim 2 , wherein the blade body includes the pressure side surface and a suction side surface, the blade body further includes a bulge at the suction side surface coincident with the recess along the blade axial chord, the bulge includes a bulge surface portion forming a portion of the suction side surface, and the bulge surface portion has a first bulge shape which deviates from a second suction side shape of surrounding portions of the suction side surface.
5 . The method of claim 1 , wherein selecting the recess height further includes selecting the recess height such that the recess height is greater than or equal to the Y-value of 0.04.
6 . The method of claim 1 , wherein the minimum span position is less than or equal to 15 percent of a blade span of the blade body and the maximum span position is greater than or equal to 90 percent of the blade span.
7 . The method of claim 1 , further comprising rotating a bladed compressor rotor of a gas turbine engine about the rotational axis, the bladed compressor rotor including the blade body with the selected recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1.
8 . The method of claim 1 , further comprising forming the rotor blade including the blade body with the selected recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1.
9 . The method of claim 1 , wherein the minimum span position is less than or equal to 40 percent of a blade span of the blade body and the maximum span position is greater than or equal to 90 percent of the blade span.
10 . The method of claim 1 , wherein the recess has a first recess shape which deviates from a second pressure side shape of surrounding portions of the pressure side surface.
11 . A method comprising:
observing a Y-Z plane orthogonal to a rotational axis of a blade body of a rotor blade, a Z-direction of the Y-Z plane extends in a span direction of the blade body, a Y-direction of the Y-Z plane extends orthogonal to the Z-direction;
intersecting the Y-Z plane with a recess forming a portion of a pressure side surface of the blade body to obtain a two-dimensional curve of a surface profile of the pressure side surface;
determining a straight-line equation for a straight line intersecting the two-dimensional curve at a minimum span position and a maximum span position for the recess; and
selecting a recess height of the recess such that the recess height is greater than or equal to a Y-value of 0.025 and less than or equal to the Y-value of 0.1, and the recess height is a maximum height measured in the Y-direction between the two-dimensional curve and the straight line between the minimum span position and the maximum span position.
12 . The method of claim 11 , wherein selecting the recess height further includes selecting the recess height within a recess axial chord of the recess extending between and to a minimum axial chord position and a maximum axial chord position, the minimum axial chord position is greater than or equal to 50 percent of a blade axial chord of the blade body and the maximum chord position is less than or equal to 80 percent of the blade axial chord.
13 . The method of claim 12 , wherein selecting the recess height further includes selecting the recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1 for a plurality of axial positions, relative to the rotational axis, between and to the minimum axial chord position and the maximum axial chord position.
14 . The method of claim 12 , wherein the blade body includes the pressure side surface and a suction side surface, the blade body further includes a bulge at the suction side surface coincident with the recess along the blade axial chord, the bulge includes a bulge surface portion forming a portion of the suction side surface, and the bulge surface portion has a first bulge shape which deviates from a second suction side shape of surrounding portions of the suction side surface.
15 . The method of claim 11 , wherein selecting the recess height further includes selecting the recess height such that the recess height is greater than or equal to the Y-value of 0.04.
16 . The method of claim 11 , wherein the minimum span position is less than or equal to 15 percent of a blade span of the blade body and the maximum span position is greater than or equal to 90 percent of the blade span.
17 . The method of claim 11 , further comprising rotating a bladed compressor rotor of a gas turbine engine about the rotational axis, the bladed compressor rotor including the blade body with the selected recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1.
18 . The method of claim 11 , further comprising forming the rotor blade including the blade body with the selected recess height greater than or equal to the Y-value of 0.025 and less than or equal to the Y-value of 0.1.
19 . The method of claim 11 , wherein the minimum span position is less than or equal to 40 percent of a blade span of the blade body and the maximum span position is greater than or equal to 90 percent of the blade span.
20 . The method of claim 11 , wherein the recess surface portion has a first recess shape which deviates from a second pressure side shape of surrounding portions of the pressure side surface.