Gas turbine engines having self-cooling seals and methods of operating the same

A method, comprising:

• operating a gas turbine engine having a first component that is directly exposed to a high temperature environment and a second component adjacent to the first component that is not directly exposed the high temperature environment;
• providing a seal between and in contact with radially opposed surfaces of the first component and the second component, the seal separating a cavity between the first component and the second component to define a higher pressure region and a lower pressure region, the seal comprising an annular body encircling a longitudinal axis of the gas turbine engine, the annular body having an S-shaped cross-section biased outwardly in a radial direction to apply forces against the first component and the second component, wherein the annular body includes a first contact portion in contact with the first component and a second contact portion in contact with the second component;
• configuring the S-shaped cross-section of the annular body to include a first end portion that includes the first contact portion, a second end portion that includes the second contact portion, and a central portion between the first end portion and the second end portion, wherein the central portion includes holes extending through the annular body;
• configuring the annular body to include a first bend between the first end portion and the central portion that is sufficient to position the first end portion and the central portion to be overlapping with the first end portion axially aft of the central portion, and to include a second bend between the second end portion and the central portion that is sufficient to position the second end portion and the central portion to be overlapping with the second end portion axially forward of the central portion;
• and
• cooling of the first contact portion of the annular body of the seal by directing a fluid flow through the holes extending through the central portion of the annular body from the higher pressure region to the lower pressure region toward the first contact portion of the annular body.

An aircraft, comprising:

• a gas turbine engine, comprising:
• a first component that is directly exposed to a high temperature environment during operation of the gas turbine engine;
• a second component adjacent to the first component, wherein the second component is not directly exposed the high temperature environment during the operation of the gas turbine engine;
• and
• a seal between and in contact with radially opposed surfaces of the first component and the second component, the seal separating a cavity between the first component and the second component to define a higher pressure region and a lower pressure region, the seal comprising:
• an annular body encircling a longitudinal axis of the gas turbine engine, the annular body having an S-shaped cross-section biased outwardly in a radial direction to apply forces against the first component and the second component, wherein the annular body includes a first contact portion in contact with the first component and a second contact portion in contact with the second component;
• and
• holes extending through the annular body that are configured to provide passage for fluid flow therethrough from the higher pressure region to the lower pressure region, wherein the holes are configured to direct the fluid flow toward the first contact portion of the annular body and thereby provide cooling of the first contact portion during the operation of the gas turbine engine,
• wherein the S-shaped cross-section of the annular body includes a first end portion that includes the first contact portion, a second end portion that includes the second contact portion, and a central portion between the first end portion and the second end portion, wherein the central portion includes the holes extending therethrough,
• wherein the first end portion is axially aft of the second end portion and extends radially inward and the second end portion is axially forward of the first end portion and extends radially outward, wherein the annular body includes a first bend between the first end portion and the central portion that is sufficient to position the first end portion and the central portion to be overlapping with the first end portion axially aft of the central portion, and the annular body includes a second bend between the second end portion and the central portion that is sufficient to position the second end portion and the central portion to be overlapping with the second end portion axially forward of the central portion, wherein the fluid flow is directed between the second end portion and the central portion, through the holes, and then between the central portion and the first end portion, wherein the holes have a central axis oriented to direct the fluid flowing through the holes directly toward a surface of the first end portion.