Method for manufacturing of a gas turbine engine component

A component of a gas turbine engine, the component comprising:

• an outer ring structure;
• an inner ring structure;
• a plurality of circumferentially spaced elements extending between the inner ring structure and the outer ring structure;
• wherein a primary gas channel for axial gas flow is defined between the elements and wherein the component has an inlet side for gas entrance and an outlet side for gas outflow;
• and
• a one-piece part comprising:
• a portion of each of said elements, wherein said portion relates to a portion of an extension length of the elements between said inner ring structure and said outer ring structure;
• and
• a ring-shaped member that connects said element portions and that forms part of one of the inner ring structure and the outer ring structure;
• wherein the element portions contribute to at least 30-40%, and at the most 60-70%, of the extension length of the elements between said ring structures.

A gas turbine engine comprising:

• a component including an outer ring structure, an inner ring structure, and a plurality of circumferentially spaced elements extending between the inner ring structure and the outer ring structure, wherein a primary gas channel for axial gas flow is defined between the elements, and wherein the component has an inlet side for gas entrance and an outlet side for gas outflow;
• wherein the component is formed from a method comprising:
• machining a one-piece metal blank as to form a one-piece part comprising:
• a portion of each of said elements, wherein said portion relates to a portion of an extension length of the elements between said inner ring structure and said outer ring structure;
• and
• a ring-shaped member that connects said element portions and that forms part of one of the inner ring structure and the outer ring structure;
• wherein the element portions contribute to at least 30%, and at the most 70%, of the extension length of the elements between said ring structures.