Gas turbine engine cooling component

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.

BACKGROUND

This disclosure relates generally to a gas turbine engine, and more particularly to a component that can be incorporated into a gas turbine engine. The component can include a cover plate for providing dedicated cooling to portions of the component.

Both the compressor and turbine sections of a gas turbine engine may include alternating rows of rotating blades and stationary vanes that extend into the core flow path of the gas turbine engine. For example, in the turbine section, turbine blades rotate and extract energy from the hot combustion gases that are communicated along the core flow path of the gas turbine engine. The turbine vanes prepare the airflow for the next set of blades. These blades and vanes are examples of components that may need cooled by a dedicated source of cooling air in order to withstand the relatively high temperatures of the hot combustion gases that are communicated along the core flow path of a gas turbine engine.

SUMMARY

In one exemplary embodiment, 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.

In a further embodiment of any of the above, a perimeter of the cover plate is attached to a land on the non-gas path side of the platform and the at least one bulge is spaced inward from a perimeter of the cover plate.

In a further embodiment of any of the above, the non-gas path side of the platform includes a feed cavity surrounding the inlet.

In a further embodiment of any of the above, the cover plate encloses the inlet.

In a further embodiment of any of the above, at least one airfoil includes a forward internal cavity located forward of the internal cavity and has an inlet spaced outward from a perimeter of the cover plate.

In a further embodiment of any of the above, the cover plate includes a pair of airfoils that each have a corresponding inlet on the non-gas path side of the platform. The cover plate includes a pair of bulges each aligned with a corresponding one of the inlets.

In a further embodiment of any of the above, the first plurality of fluid openings in the cover plate are located on a first circumferential side of the at least one bulge and a second plurality of fluid openings are located on a second circumferential side of the at least one bulge.

In a further embodiment of any of the above, the inlet is at least partially defined by a collar.

In a further embodiment of any of the above, the inlet includes a plurality of inlets and the collar at least partially surrounds each of the inlets.

In a further embodiment of any of the above, the cover plate is free of non-cooling apertures.

In a further embodiment of any of the above, the internal cavity feeds trailing edge cooling apertures on the at least one airfoil.

In another exemplary embodiment, a gas turbine engine includes a compressor section. A combustor section is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor section. One of the compressor section or the turbine section includes at least one component that has 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 to 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.

In a further embodiment of any of the above, a perimeter of the cover plate is attached to a land on the non-gas path side of the platform. At least one bulge is spaced inward from a perimeter of the cover plate.

In a further embodiment of any of the above, the non-gas path side of the platform includes a feed cavity surrounding the inlet.

In a further embodiment of any of the above, the cover plate encloses the inlet.

In a further embodiment of any of the above, at least one airfoil includes a forward internal cavity located forward of the internal cavity that has an inlet spaced outward from a perimeter of the cover plate.

In a further embodiment of any of the above, at least one airfoil includes a pair of airfoils that each have a corresponding inlet on the non-gas path side of the platform. The cover plate includes a pair of bulges each aligned with a corresponding one of the inlets.

In a further embodiment of any of the above, the first plurality of fluid openings in the cover plate are located on a first circumferential side of at least one bulge. A second plurality of fluid openings are located on a second circumferential side of the at least one bulge.

In a further embodiment of any of the above, the inlet is at least partially defined by a collar.

In a further embodiment of any of the above, the inlet includes a plurality of inlets and the collar at least partially surrounds each of the inlets.

DETAILED DESCRIPTION

FIG. 2illustrates a cross-sectional view through a high pressure turbine section54. In the example high pressure turbine section54, first and second arrays of rotating blades60,62are axially spaced apart from one another around first and second rotor disks64,66, respectively. An array of vanes68are located axially between the first and second arrays of blades60,62. The first and second arrays of blades60,62and the array of vanes68are spaced radially inward from a case structure70. It should be understood that any number of stages may be used in the example high pressure turbine section54. Moreover, the disclosed airfoils may be used in a compressor section or the turbine section.

Each blade in the first and second array of blades60,62includes an airfoil72that extends from a platform74towards a free end at a blade tip76. The blade tip76is located adjacent a blade outer air seal78that is supported by the case structure70. The blade outer air seals78provide an outer boundary of the core flow path C and the platform74provides an inner boundary of the core flow path C. The first and second arrays of the blades60,62are operatively connected to the high speed spool32, for example.

The array of vanes68include individual vanes having airfoils80that extend between a radially inner platform82and a radially outer platform84that define the core flow path C. The airfoil80includes a pressure side80P (predominantly concave—FIG. 2) and a suction side80S (predominantly convex—FIG. 3) extending between a leading edge86and a trailing edge88. The radially outer platform84includes hooks90that secure the array of vanes68relative to the case structure70. It should be understood that the array of vanes68may be discrete from one another, arranged in integrated clusters of vanes, or a continuous ring of vanes.

Each airfoil80includes multiple internal cooling circuits or cavities. In the illustrated example, the airfoil80includes a leading edge cavity94, an intermediate cavity96, and downstream cavities98. As shown inFIGS. 2 and 3, cooling air enters the intermediate cavity96through an intermediate cavity inlet96I on a radially outer side of the radially outer platform84and travels in a radially inward direction through the airfoil80and exits through an intermediate cavity outlet96E in a radially inner side of the radially inner platform82. In this disclosure, radial or radially is in relation to the engine axis A unless stated or discussed otherwise.

Cooling air enters the downstream cavities98by traveling through fluid inlets118in a cover plate100(FIGS. 4-5) and through downstream cavity inlets98I in the radially outer side of the radially outer platform84. The cooling air travels radially inward through the airfoil80until it reaches a vane inner cavity104. A portion of the cooling air entering the vane inner cavity104passes through an orifice107in an inner hoop seal106to provide cooling air to a rotor cavity109. The cooling air in the downstream cavity98adjacent the trailing edge88exits the airfoil80through cooling apertures108(FIG. 2) extending along the trailing edge88of the airfoil80.

In the illustrated example shown inFIG. 3, the array of vanes68are comprised of vane doublets having two airfoils80. The radially outer platform84includes the two intermediate cavity inlets96I to each of the intermediate cavities96in each of the airfoils80and six downstream cavity inlets98I in fluid communication with a corresponding one of the downstream cavities98.

A radially outer side or non-gas path side of the radially outer platform84includes a cover plate contact surface110. In the illustrated example, the cover plate contact surface110is located on a radially outer surface of a rib that forms a weld land surrounding a recessed cavity112. The cover plate contact surface110separates the inlet98I to an upstream one of the downstream cavities98from the inlet96I to intermediate cavity96. In the illustrated example, each of the recessed cavities112are separated from each other by the rib defining cover plate contact surface110.

In the illustrated example, the intermediate cavity inlet96I is radially aligned with and at least partially defined by the cover plate contact surface110. The downstream cavity inlets98I are spaced radially inward from the intermediate cavity inlet96I and at least partially defined by the base surface114of the recessed cavity112.

As shown inFIGS. 4-5, the cover plate100encloses the recessed cavity112to define a feed cavity for the downstream cavity inlets98I. The cover plate100includes a radially outer side100A and a radially inner side100B. The radially inner side100B is attached to cover plate contact surface110by welding, adhesive, or other means known in the art. The cover plate100is generally planar and includes bulges116circumferentially and axially aligned with the downstream cavity inlets98I and spaced radially outward from the downstream cavity inlets98I to define a fluid passageway there between.

As shown inFIG. 5, the cover plate100includes multiple fluid inlets118extending through the cover plate100to allow the cooling airflow to pass through the cover plate100as shown by arrows120. In the illustrated example, the bulges116do not include the fluid inlets118and in another example, the bulges116includes some of the fluid inlets118. Once the cooling air has passed through the fluid inlets118in the cover plate100, the cooling air collects in the recessed cavity112.

From the recessed cavity112, the cooling air enters the downstream cavity inlets98I. The cooling air enters from at least three sides of the downstream cavity inlets98I as shown by arrows122inFIG. 5, resulting in lower Mach numbers and pressure loss entering the downstream cavity inlet98I.

FIG. 6-8illustrate another example vane68A. The vane68A is similar to the vane68except where shown in the Figures or described below. Like numbers will be used between the vane68and68A but with the addition of an “A.”

In the illustrated example, each airfoil80A includes a leading edge cavity94A (not shown), an intermediate cavity96A, and a downstream cavity98A. As shown inFIG. 7-8, cooling air enters the intermediate cavity96A through an intermediate cavity inlet96IA on a radially outer side of the radially outer platform84A and travels in a radially inward direction through the airfoil80A. The cooling air travels radially inward through the airfoil80A until it reaches the vane inner cavity104(FIG. 2). A portion of the cooling air entering the vane inner cavity104can pass through the orifice107in an inner hoop seal106to provide cooling air to the rotor cavity109.

Cooling air enters the downstream cavity98A by traveling through the fluid inlets118A in the cover plate100(FIGS. 7-8) and through downstream cavity inlet98IA in the radially outer side of the radially outer platform84A. The cooling air travels radially inward and outward through the airfoil80A until it reaches the vane inner cavity104A. A collar99A on the radially outer side of the radially outer platform84A partially encloses the downstream cavity98A. A portion of the cooling air entering the vane inner cavity104can pass through the orifice107in an inner hoop seal106to provide cooling air to the rotor cavity109.

The radially outer side or non-gas path side of the radially outer platform84A includes a cover plate contact surface110A. In the illustrated example, the cover plate contact surface110A is located on a radially outer surface of a rib that forms a weld land surrounding a recessed cavity112A. The cover plate contact surface110A separates the inlet98IA of the downstream cavity98A from the inlet96IA to intermediate cavity96A. In the illustrated example, each of the recessed cavities112A are separated from each other by the rib defining cover plate contact surface110A and the collars99A extend into a corresponding one of the recessed cavities112A.

As shown inFIGS. 7-8, the cover plate100encloses the recessed cavity112A to define a feed cavity for the downstream cavity inlet98IA. The radially inner side100B is attached to cover plate contact surface110by welding, adhesive, or other means known in the art. The bulges116on the cover plate100are circumferentially and axially aligned with the downstream cavity inlets98IA and the collars99and spaced radially outward from the downstream cavity inlet98I and the collars99A to define a passageway there between.

As shown inFIG. 8, once the cooling air passes through the fluid inlets118in the cover plate100, the cooling air collects in the passageway between the cover plate100and the recessed cavity112A. From the passageway, the cooling air enters the downstream cavity inlet98IA. The cooling air can enter from at least three sides of the downstream cavity inlet98IA as shown by arrows122inFIG. 8, resulting in lower Mach numbers and pressure loss entering the downstream cavity inlet98IA.

FIG. 9-11illustrate another example vane68B. The vane68B is similar to the vane68except where shown in the Figures or described below. Like numbers will be used between the vane68and68A but with the addition of a “B.”

In the illustrated example, each airfoil80B includes a leading edge cavity94B (not shown), an intermediate cavity96B, and downstream cavities98B. As shown inFIG. 10-11, cooling air enters the intermediate cavities96B through intermediate cavity inlets96IB on a radially outer side of a radially outer platform84B and travels in a radially inward direction through the airfoil80B. The cooling air travels radially inward through the airfoil80B until it reaches a vane inner cavity104(FIG. 2). A portion of the cooling air entering the vane inner cavity104can pass through the orifice107in the inner hoop seal106to provide cooling air to the rotor cavity109(FIG. 2).

Cooling air enters the downstream cavities98B by traveling through fluid inlets118B in the cover plate100(FIGS. 9-10) and through downstream cavity inlets98IB in the radially outer side of the radially outer platform84B. The cooling air travels radially inward and outward through the airfoil80B until it reaches the vane inner cavity104B. A collar99B surrounds each of the downstream cavity inlets98IB to reduce stress caused by the intersection of the airfoil80B and the platform84B. A portion of the cooling air entering the vane inner cavity104can pass through the orifice107in an inner hoop seal106to provide cooling air to the rotor cavity109.

The radially outer side or non-gas path side of the radially outer platform84B includes a cover plate contact surface110B. In the illustrated example, the cover plate contact surface110B is located on a radially outer surface of a rib that forms a weld land surrounding a recessed cavity112B. The cover plate contact surface110B separates the inlet98IB of the downstream cavity98B from the inlet96IB to intermediate cavity96B. In the illustrated example, each of the recessed cavities112B are separated from each other by the rib defining cover plate contact surface110B and a radially outer surface of each of the collars99B is aligned with the cover plate contact surface110B. However, in the illustrated embodiment, the cover plate100is not attached to the radially outer surface of the collars99B.

As shown inFIGS. 10-11, the cover plate100encloses the recessed cavity112B to define a feed cavity for the downstream cavity inlets98IB. The radially inner side100B is attached to cover plate contact surface110by welding, adhesive, or other means known in the art. The bulges116on the cover plate100are circumferentially and axially aligned with the downstream cavity inlets98IB and the collars99B and spaced radially outward from the downstream cavity inlets98IB and the collars99B to define a passageway there between.

As shown inFIG. 11, once the cooling air passes through the fluid inlets118in the cover plate100, the cooling air collects in the passageway between the cover plate100and the recessed cavity112B. From the passageway, the cooling air enters the downstream cavity inlets98IB. The cooling air can enter from at least three sides of the downstream cavity inlets98IB as shown by arrows122inFIG. 11, resulting in lower Mach numbers and pressure loss entering the downstream cavity inlets98IB.

Although the different non-limiting embodiments are illustrated as having specific components, the embodiments of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from any of the non-limiting embodiments in combination with features or components from any of the other non-limiting embodiments.

It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed and illustrated in these exemplary embodiments, other arrangements could also benefit from the teachings of this disclosure.