Rotor for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11060406-B2
Application number	US-201916599798-A
Country	US
Kind code	B2
Filing date	Oct 11, 2019
Priority date	Oct 11, 2019
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

First claim

The invention claimed is:

1. A rotor for an aircraft engine, comprising:
a hub having a rotation axis;
a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members each having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections being defined by opposite edges of the corresponding structural member of the structural members; and a circumferential array of airfoils extending radially outward from the annular ring.

2. The rotor of claim 1 , wherein the rotor is one of a turbine rotor for a turbine section of the aircraft engine and a compressor rotor for a compressor section of the aircraft engine.

3. The rotor of claim 1 , wherein the structural members are shaped such that for a given one of the structural members, cross-sections of the given structural member taken at least through a portion of the given structural member at decreasing radial distances from the rotation axis are correspondingly more aligned with a plane of rotation of the hub.

4. The rotor of claim 3 , wherein the structural members are shaped such that for the given one of the structural members, cross-sections of the given structural member taken through an entire radial length of the given structural member at the decreasing radial distances from the rotation axis are correspondingly more aligned with the plane of rotation of the hub.

5. The rotor of claim 4 , wherein the hub includes a central portion having a first thickness measured parallel to the rotation axis, and a disc extending radially away from the central portion parallel to a plane of rotation of the hub, the disc has a second thickness measured parallel to the rotation axis, the second thickness is smaller than the first thickness, and the structural members connect to the disc.

6. The rotor of claim 5 , wherein the disc has a first diameter defined by a radially-outer periphery and measured in a plane of rotation of the hub, the annular ring has a second diameter measured in the plane of rotation, and the first diameter is between 25% and 75% of the second diameter.

7. The rotor of claim 6 , wherein the first diameter is between 30% and 70% of the second diameter.

8. The rotor of claim 1 , wherein the structural members are at least in part airfoil shaped.

9. The rotor of claim 3 , wherein the cross-sections of the structural members contacting the annular ring are angled between 10 and 60 degrees relative to the rotation axis.

10. The rotor of claim 9 , wherein the cross-sections of the structural members contacting the hub are angled between 60 and 90 degrees relative to the rotation axis.

11. The rotor of claim 1 , wherein a width of the cross-sections varies along at least a portion of the structural members.

12. The rotor of claim 1 , wherein the airfoils define a part of a first airflow path fluidly connecting a compressor section and a turbine section, and the structural members define a second airflow path extending through a part of the aircraft engine and being different from the first airflow path.

13. The rotor of claim 1 , wherein the rotor is a plurality of rotors.

14. The rotor of claim 1 , wherein radially-inner cross-sections of the structural members are defined by four sides interconnected by convex portions.

Assignees

• Pratt & Whitney Canada

Inventors

• Zeinalov Jamal
• Ho Eric

Classifications

• F04D19/022

  with concentric rows of vanes; · CPC title

• F05D2240/301

  Cross-sectional characteristics · CPC title

• F01D5/141 Primary

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

• F04D29/668

  damping or preventing mechanical vibrations · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title