Rotor blade arrangement
A bladed disc comprising a disc hub; a set of blades angularly distributed around the disc hub; wherein there is variation in a geometric parameter between the blades. The blades are positioned around the disc hub such that for a majority of pairs of neighbouring blades in the set, an interval between values of the geometric parameter between the blades of the pair is less than 0.5 standard deviations of the geometric parameter for the set of blades.
1. A bladed disc comprising:
a disc hub; and
a set of blades angularly distributed around the disc hub; wherein
there is variation in a geometric parameter between the blades;
the blades are positioned around the disc hub such that for a majority of pairs of neighbouring blades in the set, an interval between values of the geometric parameter between the blades of the pair is less than 0.5 standard deviations of the geometric parameter for the set of blades;
the set of blades comprises a rising subset of at least three neighbouring blades in which there is an increasing trend of the geometric parameter in a first angular direction around the disc hub;
the set of blades comprises a falling subset of at least three neighbouring blades in which there is a decreasing trend of the geometric parameter in the first angular direction; and
the rising subset includes a blade having a value of the geometric parameter less than a median value of the geometric parameter in the set of blades and a blade having a value of the geometric parameter more than the median value, and/or the falling subset includes a blade having a value of the geometric parameter less than the median value and a blade having a value of the geometric parameter more than the median value.
2. The bladed disc of claim 1 , wherein each blade in the rising subset has a higher value of the geometric parameter than its previous neighbour in the rising subset; and
wherein each blade in the falling subset has a lower value of the geometric parameter than its previous neighbour in the falling subset.
3. The bladed disc of claim 1 , wherein each blade in the set of blades belongs to either a rising subset or a falling subset.
4. The bladed disc of claim 2 , wherein there is a single rising subset and a single falling subset in the set of blades, and the angular gaps between all neighbouring blades in the set of blades sum to 360°.
5. The bladed disc of claim 1 , wherein a maximum interval in the geometric parameter between two neighbouring blades in the set of blades is 100% or less of a standard deviation of the geometric parameter in the set of blades.
6. The bladed disc of claim 1 , wherein the geometric parameter is a stagger angle of the blade.
7. The bladed disc of claim 6 , wherein the stagger angle is an untwisted stagger angle corresponding to a centrifugal loading condition of the blade.
8. The bladed disc of claim 1 , wherein the geometric parameter is selected from the group consisting of:
a stagger angle of the blade, such as an untwisted stagger angle corresponding to a centrifugal loading condition of the blade;
a thickness of the blade at one or more predetermined measurement points, including at a trailing edge portion, at a mean aerodynamic chord, or at a leading edge portion;
a camber line angle at the trailing edge;
a camber line angle at the leading edge
a curvature of a suction surface of the blade;
a curvature of a pressure surface of the blade.
9. A gas turbine engine comprising a bladed disc of claim 1 .
10. A method of assembling a bladed disc, the method comprising the steps of:
providing a set of blades;
determining a geometric parameter of each blade of the set of blades;
determining assembly positions around a disc hub for each blade of the set of blades of the plurality, based on the geometric parameter; and
assembling each blade of the set of blades in its respective assembly position to provide a bladed disc of claim 1 .
11. The method of claim 10 , wherein the geometric parameter is determined whilst each respective blade is in a centrifugal loading condition.
12. The method of claim 10 , wherein the geometric parameter is determined by modal analysis of the blade.
13. The method of claim 10 , wherein the geometric parameter is a simulated geometric parameter of the blade in a centrifugal loading condition, and wherein the simulated geometric parameter is simulated based on a relationship with one or more measured geometric or structural parameters of the blade in an unloaded condition.
14. The method of claim 13 , wherein the one or more measured geometric parameters are selected from the group consisting of:
a stagger angle of the blade;
a thickness of the blade at one or more predetermined measurement points including at a trailing edge portion, at a mean aerodynamic chord, or at a leading edge portion;
a camber line angle at the trailing edge;
a camber line angle at the leading edge
a curvature of a suction surface of the blade; and
a curvature of a pressure surface of the blade.
15. The method of claim 10 , wherein the geometric parameter is selected from the group consisting of:
a stagger angle of the blade, such as an untwisted stagger angle corresponding to a centrifugal loading condition of the blade;
a thickness of the blade at one or more predetermined measurement points including at a trailing edge portion, at a mean aerodynamic chord, or at a leading edge portion;
a camber line angle at the trailing edge;
a camber line angle at the leading edge
a curvature of a suction surface of the blade; and
a curvature of a pressure surface of the blade.
16. The bladed disc of claim 1 , wherein a maximum interval in the geometric parameter between two neighbouring blades in the set of blades is 75% or less of a standard deviation of the geometric parameter in the set of blades.
17. The bladed disc of claim 1 , wherein a maximum interval in the geometric parameter between two neighbouring blades in the set of blades is 50% or less of a standard deviation of the geometric parameter in the set of blades.