Blade tip for ceramic matrix composite blade

Patent metadata

Field	Value
Publication number	US-11085302-B2
Application number	US-201815926585-A
Country	US
Kind code	B2
Filing date	Mar 20, 2018
Priority date	Mar 20, 2018
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

Turbine blades for use in gas turbine engines are disclosed herein. Each blade includes an airfoil and a protective crown. The airfoil includes ceramic matrix composite materials. The protective crown includes ceramic-containing materials and is mounted to a radially-outer end portion of the airfoil.

First claim

What is claimed is:

1. A turbine blade adapted for use in a gas turbine engine, the turbine blade comprising
an airfoil comprising ceramic matrix composite materials including ceramic-containing reinforcements suspended in ceramic-containing matrix material, the airfoil having a radially-inner end portion, a radially-outer end portion, and a body portion that extends from the radially-inner end portion to the radially-outer end portion,
a protective crown comprising entirely ceramic-containing materials mounted to the radially-outer end portion of the airfoil, the protective crown configured to provide a radially-outermost surface of the turbine blade such that the protective crown is positioned to engage a blade track or other structure radially outward of the airfoil upon use of the turbine blade in the gas turbine engine so that the ceramic matrix composite materials of the airfoil are protected from rub that could remove barrier coatings and expose the ceramic matrix materials of the airfoil to the environment which can damage the ceramic matrix materials of the airfoil, and
a crown retainer configured to block motion of the protective crown in a radial direction relative to the airfoil, the crown retainer including a flange incorporated into either the airfoil or the protective crown that is received in a flange-receiving channel formed in the other of the airfoil or the protective crown,
wherein the ceramic containing materials of the protective crown are different from the ceramic matrix composite materials of the airfoil, wherein the protective crown, wherein the outermost surface forms a squealer tip having an axially extending first side rail portion and an axially extending second side rail portion, and a cavity extends circumferentially between the axially extending first side rail portion and the axially extending second side rail portion, wherein the protective crown is shaped to include a tip portion that extends radially outward of the airfoil to provide the radially-outermost surface of the turbine blade and a tip mount that radially overlaps the radially-outer end portion of the airfoil, wherein the flange of the crown retainer is incorporated into the protective crown and the flange-receiving channel of the crown retainer is formed in the airfoil, and wherein the tip mount of the protective crown is received in a mount aperture extending in the radial direction through the radially-outer end portion of the airfoil and the flange-receiving channel extends into the radially-outer end portion or the body portion of the airfoil from the mount aperture, and the flange extends outwardly from the tip mount into the flange-receiving channel.

2. The turbine blade of claim 1 , wherein the crown retainer, and the airfoil are co-processed together to form an integral, single-piece component.

3. The turbine blade of claim 2 , wherein the protective crown comprises entirely monolithic ceramic materials.

4. The turbine blade of claim 3 , wherein the protective crown provides the entirety of the radially outer-most surface of the turbine blade.

5. The turbine blade of claim 1 , wherein the protective crown provides the entirety of the radially outer-most surface of the turbine blade.

6. The turbine blade of claim 1 , wherein the protective crown comprises entirely monolithic ceramic materials.

7. A turbine blade adapted for use in a gas turbine engine, the turbine blade comprising
an airfoil comprising ceramic matrix composite materials including ceramic-containing reinforcements suspended in ceramic-containing matrix material, the airfoil having a radially-inner end portion, a radially-outer end portion, and a body portion that extends from the radially-inner end portion to the radially-outer end portion,
a protective crown comprising entirely ceramic-containing materials mounted to the radially-outer end portion of the airfoil, the protective crown configured to provide a radially-outermost surface of the turbine blade such that the protective crown is positioned to engage a blade track or other structure radially outward of the airfoil upon use of the turbine blade in the gas turbine engine so that the ceramic matrix composite materials of the airfoil are protected from rub that could remove barrier coatings and expose the ceramic matrix materials of the airfoil to the environment which can damage the ceramic matrix materials of the airfoil, and
a crown retainer configured to block motion of the protective crown in a radial direction relative to the airfoil, the crown retainer including a flange incorporated into either the airfoil or the protective crown that is received in a flange-receiving channel formed in the other of the airfoil or the protective crown,
wherein the ceramic containing materials of the protective crown are different from the ceramic matrix composite materials of the airfoil, wherein the outermost surface forms a squealer tip having an axially extending first side rail portion and an axially extending second side rail portion, and a cavity extends circumferentially between the axially extending first side rail portion and the axially extending second side rail portion, wherein the protective crown is shaped to include a tip portion that extends radially outward of the airfoil to provide the radially-outermost surface of the turbine blade and a tip mount that radially overlaps the radially-outer end portion of the airfoil, wherein the flange of the crown retainer is incorporated into the airfoil and the flange-receiving channel of the crown retainer is formed in the protective crown, and wherein the radially-outer end portion of the airfoil comprises a central stud extending radially outward of the body portion of the airfoil and the flange extends outwardly from the central stud, and the tip mount of the protective crown includes a mount aperture that receives the central stud of the airfoil and the flange-receiving channel extends into the tip mount from the mount aperture and around the flange.

8. The turbine blade of claim 7 , wherein the crown retainer, and the airfoil are co-processed together to form an integral, single-piece component.

9. The turbine blade of claim 8 , wherein the protective crown comprises entirely monolithic ceramic materials.

10. The turbine blade of claim 9 , wherein the protective crown provides the entirety of the radially outer-most surface of the turbine blade.

11. The turbine blade of claim 7 , wherein the protective crown provides the entirety of the radially outer-most surface of the turbine blade.

12. The turbine blade of claim 7 , wherein the protective crown comprises entirely monolithic ceramic materials.

13. A turbine blade adapted for use in a gas turbine engine, the turbine blade comprising
an airfoil comprising ceramic matrix composite materials including ceramic-containing reinforcements suspended in ceramic-containing matrix material, the airfoil having a radially-inner end portion, a radially-outer end portion, and a body portion that extends from the radially-inner end portion to the radially-outer end portion,
a protective crown comprising entirely ceramic-containing materials mounted to the radially-outer end portion of the airfoil, the protective crown configured to provide a radially-outermost surface of the turbine blade such that the protective crown is positioned to engage a blade track or other structure radially outward of the airfoil upon use of the turbine blade in the gas turbine engine so that the ceramic matrix composite materials of the airfoil are protected from rub that could remove barrier coatings and expose the ceramic matrix materials of the airfoil to the environment which c

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce High Temperature Composites Inc

Inventors

• Freeman Ted J
• Roehm Jeremy P
• Shinavski Robert J

Classifications

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/22

  Blade-to-blade connections, {e.g. for damping vibrations} · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title