Rotor with subset of blades having a cutout leading edge

Patent metadata

Field	Value
Publication number	US-10584591-B2
Application number	US-201816031340-A
Country	US
Kind code	B2
Filing date	Jul 10, 2018
Priority date	Jul 14, 2017
Publication date	Mar 10, 2020
Grant date	Mar 10, 2020

Abstract

A rotor of a turbomachine includes a plurality of rotor blades, which each have a blade leading edge and a tip, the rotor blades forming a first group and at least one further group of rotor blades of different construction. It is provided that the rotor blades of the first group are nominal rotor blades, the rotor blades of the at least one further group each have a material cutout in the transition from the blade leading edge to the tip, the material cutout not being present in the case of the rotor blades of the first group, and the rotor blades of the first group and of the at least one further group form a non-periodic sequence in a circumferential direction.

First claim

The invention claimed is:

1. A rotor of a turbomachine, comprising:
a plurality of rotor blades, each including a blade leading edge and a tip,
the plurality of rotor blades forming a first group and at least one further group of rotor blades of different construction,
wherein
the rotor blades of the first group are nominal rotor blades,
the rotor blades of the at least one further group each have a material cutout in a transition from the blade leading edge to the tip, the material cutout being omitted in the rotor blades of the first group, and
the rotor blades of the first group and the at least one further group form a non-periodic sequence in a circumferential direction;
wherein, in the rotor blades with material cutouts, a cross-sectional shape of the blade leading edge as viewed in a radial direction in a region along the material cutout deviates from a cross-sectional shape of the blade leading edge as viewed in the radial direction in a region outside the material cutout;
wherein the blade leading edge has an obtuse form in the region along the material cutout, and an elliptical form in the region outside the material cutout;
or
wherein the blade leading edge has an elliptical form in the region along the material cutout and in the region outside the material cutout, a ratio of major axis to minor axis being greater in the region along the material cutout than in the region outside the material cutout.

2. The rotor according to claim 1 , wherein the rotor blades form two groups of different construction, the rotor blades of the first group being the nominal rotor blades and the rotor blades of the at least one further group being the second group.

3. The rotor according to claim 1 , wherein the rotor blades form n groups, n≥3, of different construction, the rotor blades of the first group being the nominal rotor blades, and the rotor blades of each further group of the at least one further group being rotor blades which have material cutouts in the transition from the blade leading edge to the tip, with at least one chosen from a shape and a dimension of the material cutout of the rotor blades being different in each further group.

4. The rotor according to claim 3 , wherein the further groups with material cutouts differ by having, with respect to the radial direction, a differently steep profile of the blade leading edge in the region along the material cutout.

5. The rotor according to claim 4 , wherein the rotor blades form three groups of different construction, the rotor blades of the first group being the nominal rotor blades and the rotor blades of a second group and a third group being rotor blades which have material cutouts in the transition from the blade leading edge to the tip, the material cutouts, with respect to the radial direction, having a steeper profile of the blade leading edge in the rotor blades of the second group than in the rotor blades of the third group.

6. The rotor according to claim 1 , wherein the material cutouts are at least approximately triangular shaped in side view, with a longest side of the triangle forming the blade leading edge of the rotor blade in the region along the material cutout.

7. The rotor according to claim 1 , wherein, where there are two groups of rotor blades with material cutouts, a flatter blade leading edge shape is formed in one of the two groups which has a lesser steepness profile of the blade leading edge in the region along the material cutout.

8. The rotor according to claim 1 , wherein the blade leading edge has a semicircular form in the region along the material cutout, and an elliptical form in the region outside the material cutout.

9. The rotor according to claim 1 , wherein the blade leading edge has an obtuse form in the region along the material cutout, and an elliptical form in the region outside the material cutout.

10. The rotor according to claim 1 , wherein the blade leading edge has an elliptical form in the region along the material cutout and in the region outside the material cutout, a ratio of major axis to minor axis being greater in the region along the material cutout than in the region outside the material cutout.

11. The rotor according to claim 1 , wherein, where there is at least one group of rotor blades with material cutouts, the shape of the blade leading edge becomes increasingly flatter with an increasing radial height in the region along the material cutout.

12. The rotor according to claim 1 , wherein the plurality of rotor blades is an uneven number of rotor blades, with a non-periodic sequence of the plurality of rotor blades being formed by a quasi-periodic sequence which is periodic apart from a break in symmetry.

13. The rotor according to claim 1 , wherein the rotor has two groups of rotor blades and the plurality of rotor blades is an even number of rotor blades, with a non-periodic sequence of the rotor blades being formed by at least one deviation from an alternating sequence.

14. The rotor according to claim 1 , wherein the rotor has a BLISK configuration.

15. The rotor according to claim 1 , wherein the rotor is a fan having a BLISK configuration.

16. The rotor according to claim 1 , wherein the rotor is a rotor of a compressor input stage of a compressor, with the rotor having a BLISK configuration.

17. A turbofan engine having a rotor according to claim 1 .

18. A rotor of BLISK configuration of a turbomachine, comprising:
an uneven number of rotor blades, each including a blade leading edge and a tip,
the rotor blades forming a first group and at least one further group of rotor blades of different construction,
the rotor blades of the first group being nominal rotor blades,
the rotor blades of the at least one further group each having a material cutout in a transition from the blade leading edge to the tip, the material cutout being omitted in the rotor blades of the first group, and
the rotor blades of the first group and the at least one further group forming a non-periodic sequence in a circumferential direction;
wherein, in the rotor blades with material cutouts, a cross-sectional shape of the blade leading edge as viewed in a radial direction in a region along the material cutout deviates from a cross-sectional shape of the blade leading edge as viewed in the radial direction in a region outside the material cutout;
wherein, where there is at least one group of rotor blades with material cutouts, the shape of the blade leading edge becomes increasingly flatter with an increasing radial height in the region along the material cutout.

19. A rotor of BLISK configuration of a turbomachine, comprising:
a plurality of rotor blades, each including a blade leading edge and a tip,
the plurality of rotor blades forming a first group and at least two further groups of rotor blades of different construction,
the rotor blades of the first group being nominal rotor blades,
the rotor blades of the at least two further groups each having a material cutout in a transition from the blade leading edge to the tip, the material cutout being omitted in the rotor blades of the first group,
the rotor blades of the first group and of the at least two further groups forming a non-periodic sequence in a circumferential direction, and
wherein, in the at least two further groups of rotor blades with material cutouts, the blade leading edge, with respect to a radial direction, has a differently steep profile in a region along the material cutout than in a region outside the material cutout;
wherein, where there are two g

Assignees

• Rolls Royce Deutschland Ltd & Co Kg
• Rolls Royce Plc

Inventors

• Opoka Maciek
• Giersch Thomas
• Mueck Bernhard
• Dodds John
• Hall Chris

Classifications

• F05D2220/32

  in gas turbines · CPC title

• F04D29/324

  Blades · CPC title

• F05D2250/141

  circular · CPC title

• F04D29/666

  by means of rotor construction or layout, e.g. unequal distribution of blades or vanes · CPC title

• F01D5/141 Primary

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title