Tailoring rotor blade coating to tune gas turbine engine bladed rotor

Patent metadata

Field	Value
Publication number	US-12366166-B2
Application number	US-202318388259-A
Country	US
Kind code	B2
Filing date	Nov 9, 2023
Priority date	Nov 9, 2023
Publication date	Jul 22, 2025
Grant date	Jul 22, 2025

Abstract

An apparatus is provided for a gas turbine engine. This apparatus includes a bladed rotor rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk. The rotor blades are arranged circumferentially around the rotor disk in an array. The array of the rotor blades are divided into a plurality of sectors including a first sector and a second sector. The rotor blades are disposed in the first sector including a plurality of first rotor blades. Each of the first rotor blades includes a first coating. The rotor blades are disposed in the second sector including a plurality of second rotor blades. Each of the second rotor blades includes a second coating that is different from the first coating.

First claim

What is claimed is:

1. An apparatus for a gas turbine engine, comprising:
a bladed rotor rotatable about an axis, the bladed rotor including a rotor disk and a plurality of rotor blades projecting radially out from the rotor disk;
each of the plurality of rotor blades including an airfoil and a coating over the airfoil;
the plurality of rotor blades arranged circumferentially around the rotor disk into a plurality of blade groupings including a plurality of first blade groupings and a plurality of second blade groupings, each of the plurality of first blade groupings disposed circumferentially between a respective circumferentially neighboring pair of the plurality of second blade groupings, and each of the plurality of second blade groupings disposed circumferentially between a respective circumferentially neighboring pair of the plurality of first blade groupings;
the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings having a first configuration; and
the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings having a second configuration that is different than the first configuration.

2. An apparatus for a gas turbine engine, comprising:
a bladed rotor rotatable about an axis, the bladed rotor including a rotor disk and a plurality of rotor blades arranged circumferentially around and connected to the rotor disk;
the plurality of rotor blades including a first rotor blade, a second rotor blade and a third rotor blade arranged circumferentially between and neighboring the first rotor blade and the second rotor blade;
the first rotor blade comprising a first coating;
the second rotor blade comprising a second coating that is different than the first coating; and
the third rotor blade comprising a third coating that is identical to the first coating.

3. The apparatus of claim 2 , wherein
the plurality of rotor blades further includes a fourth rotor blade;
the second rotor blade is arranged circumferentially between and neighbors the third rotor blade and the fourth rotor blade; and
the fourth rotor blade comprises a fourth coating that is identical to the second coating.

4. The apparatus of claim 2 , wherein
each of the plurality of rotor blades has a reference location;
the first coating has a first thickness at the reference location;
the second coating has a second thickness at the reference location that is different than the first thickness; and
the third coating has a third thickness at the reference location that is equal to the first thickness.

5. The apparatus of claim 1 , wherein
the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings has a first material makeup;
the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings has a second material makeup that is different than the first material makeup.

6. The apparatus of claim 1 , wherein
each of the plurality of rotor blades has a reference location;
the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings has a first thickness at the reference location; and
the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings has a second thickness at the reference location that is different than the first thickness.

7. The apparatus of claim 6 , wherein
each of the plurality of rotor blades projects radially out from the rotor disk to a tip; and
the reference location is disposed at the tip.

8. The apparatus of claim 6 , wherein
each of the plurality of rotor blades projects radially out from the rotor disk to a tip; and
the reference location is an intermediate location between the rotor disk and the tip.

9. The apparatus of claim 6 , wherein the reference location is disposed adjacent the rotor disk.

10. The apparatus of claim 6 , wherein
each of the plurality of rotor blades extends longitudinally between a leading edge and a trailing edge; and
the reference location is disposed at the leading edge.

11. The apparatus of claim 6 , wherein
each of the plurality of rotor blades extends longitudinally between a leading edge and a trailing edge; and
the reference location is disposed at the trailing edge.

12. The apparatus of claim 6 , wherein
each of the plurality of rotor blades extends longitudinally between a leading edge and a trailing edge; and
the reference location is an intermediate location between the leading edge and the trailing edge.

13. The apparatus of claim 1 , wherein at least one of
the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings is uniformly applied with each of the plurality of rotor blades in each of the plurality of first blade groupings; or
the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings is uniformly applied with each of the plurality of rotor blades in each of the plurality of second blade groupings.

14. The apparatus of claim 1 , wherein
the coating of each of the plurality of rotor blades in each of the plurality of first blade groupings is uniformly applied with each of the plurality of rotor blades in each of the plurality of first blade groupings; and
the coating of each of the plurality of rotor blades in each of the plurality of second blade groupings is non-uniformly applied with each of the plurality of rotor blades in each of the plurality of second blade groupings.

15. The apparatus of claim 1 , wherein the bladed rotor is configured as an integrally bladed rotor.

16. The apparatus of claim 1 , wherein the bladed rotor is configured as a turbine rotor for the gas turbine engine.

17. The apparatus of claim 2 , wherein the bladed rotor is configured as an integrally bladed rotor.

18. The apparatus of claim 2 , wherein the bladed rotor is configured as a turbine rotor for the gas turbine engine.

Assignees

• Pratt & Whitney Canada

Inventors

• Dorsamy Yashiva
• Boyer Philippe
• Grewal Jasrobin
• Mittal Prakul
• Di Florio Domenico

Classifications

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F01D5/34 Primary

  Rotor-blade aggregates of unitary construction {, e.g. formed of sheet laminae; (discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282)} · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• F01D5/16

  for counteracting blade vibration · CPC title