Gas turbine engine component

Patent metadata

Field	Value
Publication number	US-9617857-B2
Application number	US-201314141109-A
Country	US
Kind code	B2
Filing date	Dec 26, 2013
Priority date	Feb 23, 2013
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

Embodiments are disclosed of a turbomachinery component having an outer part that is captured between a cap and a base of the component. In one form, the outer part is placed in compression between the cap and the base. The outer part can be formed prior to being placed between the cap and the base. In some forms, the outer part can be formed partially or completely while engaged with the component. A fugitive spacer can be placed between the outer part and an extension of the component. In various embodiments, the extension can reach into an opening of the outer part and the cap can be coupled with the extension.

First claim

What is claimed is:

1. An apparatus comprising:
a rotatable turbomachinery blade component having an inner core extending from a base and made from a first material;
an outer flow surface made from a second material and captured between the base and a cap that is fastened to the core, the core extending substantially into an interior of the outer flow surface; and
a fugitive spacer placed between the inner core and the outer flow surface, the fugitive spacer structured to be removed by heating,
wherein the first material is metallic and the second material includes is a ceramic matrix composite.

2. The apparatus of claim 1 , wherein the first material is different than the second material.

3. The apparatus of claim 1 , wherein the rotatable turbomachinery blade component is a turbine blade component, and wherein the fugitive spacer is structured to be removed through pyrolysis.

4. The apparatus of claim 3 , wherein the turbine blade component is an integral rotor and blade.

5. The apparatus of claim 1 wherein the outer flow surface comprises a green article forming a flow path surface, the fugitive spacer disposed between the inner core and the green article.

6. The apparatus of claim 5 , wherein the fugitive spacer is composed of a material capable of being pyrolyzed.

7. The apparatus of claim 5 , wherein the green article includes a ceramic.

8. The apparatus of claim 7 , wherein the green article is a ceramic matrix composite.

9. A method comprising:
forming a gas turbine engine airflow component having a component core including:
arranging an airflow surface member having an internal opening around a component core of the gas turbine engine airflow component, the component core extending substantially through the airflow surface member;
fastening an end cap to the component core; and
engaging the gas turbine engine airflow component with a fugitive agent capable of being removed during a manufacturing process to form a space between the airflow surface member and the component core.

10. The method of claim 9 , wherein the airflow surface member includes a radially inner end and a radially outer end, wherein the fastening is located on a portion of the component core that extends past the radially inner end of the airflow surface member, and wherein the airflow surface member includes a ceramic and the gas turbine engine airflow component is metallic.

11. The method of claim 9 , wherein the airflow surface member is a blade surface airflow member, wherein the gas turbine engine airflow component is a gas turbine engine blade component; and
wherein the inserting includes forming a surface of the airflow surface member, and which further includes:
processing the airflow surface member to form a finished airflow surface member; and
wherein the fastening includes fastening the end cap to the component core wherein the airflow member is placed in compression by the end cap.

12. The method of claim 9 , which further includes extruding the flow path surface component, and wherein the fastening includes one of mechanically fastening and metal joining.

13. The method of claim 9 , wherein the end cap includes a turbine tip seal and which further includes firing the airflow surface member.

14. A method comprising:
building a gas turbine engine airflow component having an outer flow surface and an inner core formed of a metallic, the building including:
placing a fugitive spacer adjacent the inner core;
forming the outer flow surface of ceramic matrix composite around the inner core, wherein the fugitive spacer is between the inner core and the outer flow surface; and
heating the gas turbine engine airflow component to remove the fugitive spacer.

15. The method of claim 14 , wherein the placing includes coating the inner core with the fugitive spacer.

16. The method of claim 14 , wherein the gas turbine engine airflow component is a blade of a turbomachinery component, and wherein the outer flow surface includes a ceramic.

17. The method of claim 14 , wherein the forming includes free form fabricating the outer flow surface, and wherein the heating includes decomposing the fugitive spacer through pyrolysis and shrinking the gas turbine engine airflow component.

18. The method of claim 14 , wherein the heating includes thermally processing the outer flow surface, wherein the outer flow surface includes a ceramic.

Assignees

• Rolls Royce Corp

Inventors

• Shuck Quinlan Y

Classifications

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• B23P15/04

  turbine or like blades from several pieces · CPC title

• Y10T29/49321

  Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic