Gas turbine engine cooling component
AssigneeUnited Technologies Corporation
InventorsBrandon W. Spangler, Adam P. Generale, Ky H. Vu
Life of this patent
Estimating the term…
Abstract
A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.
Claims16
A component for a gas turbine engine comprising:
- a platform having a gas path side and a non-gas path side;
- at least one airfoil extending from the gas path side of the platform, wherein the at least one airfoil includes an internal cavity having an inlet on the non-gas path side of the platform, wherein the internal cavity feeds trailing edge cooling apertures on the at least one airfoil;
- and
- a cover plate located adjacent the non-gas path side of the platform, the cover plate including:
- a first plurality of fluid openings extending through the cover plate;
- and
- at least one bulge at least partially aligned with the inlet.
A component for a gas turbine engine comprising:
- a platform having a gas path side and a non-gas path side;
- a pair of airfoil extending from the gas path side of the platform, wherein each of the pair of airfoils includes an internal cavity having an inlet on the non-gas path side of the platform;
- and
- a cover plate located adjacent the non-gas path side of the platform, the cover plate including:
- a first plurality of fluid openings extending through the cover plate;
- and
- at least one bulge at least partially aligned with the inlet, wherein the cover plate includes a pair of bulges each aligned with a corresponding one of the inlets.
A gas turbine engine, comprising:
- a compressor section;
- a combustor section in fluid communication with said compressor section;
- a turbine section in fluid communication with said combustor section;
- wherein one of the compressor section or the turbine section includes at least one component having:
- a platform having a gas path side and a non-gas path side;
- at least one airfoil extending from the gas path side of the platform, wherein the at least one airfoil includes an internal cavity having an inlet on the non-gas path side of the platform, wherein the inlet is at least partially defined by a collar;
- and
- a cover plate located adjacent the non-gas path side of the platform, the cover plate including:
- a first plurality of fluid openings extending through the cover plate and in fluid communication with the inlet;
- and
- at least one bulge at least partially aligned with the inlet.
Dependencies are inferred from the claim text.