Ceramic casting core having an integral vane internal core and shroud backside shell for vane segment casting
A cast ceramic core (110), including: an airfoil portion (116) shaped to define an inner surface (56) of an airfoil (52) of a vane segment (50); and a shell portion (122) having a backside-shaping surface (120) shaped to define a backside surface (68) of a shroud (62) of the vane segment. The backside-shaping surface has a higher elevation (132) and a lower elevation (134). The higher elevation is set apart from a nearest point (138) on the airfoil portion by the lower elevation. The airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.
The invention is related to casting of a cooled vane segment used in a gas turbine engine. Specifically, the invention relates to a monolithic ceramic casting core having a conventional core portion used to form an internal cooling channel in the airfoil of the vane segment plus a shroud external shell portion used to form a backside surface of the shroud of the vane segment.
BACKGROUND OF THE INVENTIONIndustrial gas turbine engine include a compressor for compressing air, a combustor arrangement for combusting a mixture of fuel and the compressed air, and a turbine for extracting energy from the combustion gases. The turbine section includes rows of blades secured to a rotor shaft, all of which are turned by the combustion gases in the energy extraction process. Between the rows of turbine blades are rows of stationary vanes that properly orient the combustion gases as the combustion gases travel within the turbine. Each row of vanes includes vane segments, each of which has an inner shroud and an outer shroud secured to opposite ends of at least one airfoil. In many turbines the airfoils may be cooled via an internal cooling channel and backsides of the shrouds may also be cooled. These cooled airfoils may be part of the first and even second rows of turbine blades. Cooling may include convective cooling via a flow of cooling air over the surface to be cooled, and/or impingement cooling via an impingement plate inserts placed inside the airfoil's internal cooling channel and adjacent the backside of the shroud.
The airfoil and shrouds may be cast together thereby forming a monolithic vane segment. Alternately, the airfoil and shrouds may be case separately and then welded together. The airfoil's internal channel requires the use of a ceramic core to create the channel and define the internal surface configuration during the casting process. The remainder of the vane segment surfaces, including those of the inner and outer shrouds, is typically defined by a ceramic shell that is formed around a wax pattern of the vane segment, where the wax pattern is formed around the ceramic core. The wax pattern is then removed, leaving a void in the shape of the vane segment, where the ceramic core defines surface of the airfoil's interior channel and the ceramic shell defines the remainder of the surface of the vane segment.
Small features are desirable on some of the surfaces of the vane segment, including the airfoil's internal channel and the backside surface of the shroud, because they can be used in conjunction with impingement jets to improve the impingement cooling. The small features can be readily formed in the surface of the airfoil's internal channel by the ceramic core because the small features on the ceramic core survive the steps leading to the final casting, and are impressed directly onto the final vane segment. The small features on the backside surface of the shroud, however, would be formed by the wax pattern, since the wax pattern defines the backside surface of the shroud. The wax pattern is a soft material. For this reason if the small features are impressed on the surface of the wax pattern and then subject to the dipping process, during which the ceramic shell is formed, the small features are distorted and/or lost. Since small features in wax patterns cannot survive the dipping process, the surfaces of the vane segment that are defined by the shell, (which are, in turn, defined by the wax pattern), cannot have small features when the small features would result from a wax pattern that is exposed to the dipping process.
One technique that has been used to overcome this problem is to use a separately-cast, discrete ceramic insert to form the small features on the shroud backside surfaces. The wax pattern is formed around the ceramic core and the ceramic insert and the shell removed, leaving a void for the vane segment. In this method the ceramic core define the airfoil's internal surface and its small features, and the ceramic insert defines the shroud backside surface and its small features, and the remainder of the vane segment surface is formed by the shell. However, the position of the ceramic insert is difficult to control precisely and the quality of the casting is less than acceptable when a ceramic insert is used. For the foregoing reasons there is room in the art for improvement.
The invention is explained in the following description in view of the drawings that show:
The present inventors have devised a unique method and integral casting core through which fine features can be formed on a backside of a shroud of a cooled vane segment when an airfoil portion and the shroud portion (or portions) of the vane segment are simultaneously cast to form a monolithic, cooled, cast vane segment. The fine features may be heat transfer features that can be used in conjunction with impingement cooling jets to more effectively cool the shroud backsides. The method and casting core are enabled in some embodiments through the use of a flexible core die liner. The flexible liner makes it possible to incorporate features into a surface of a casting that are not possible when a rigid core die is used. This is because rigid core dies must be separated along a pull plane. When the die must be pulled apart while sliding along a surface of the casting the two surfaces cannot be shaped such that they interfere with that sliding. Due to the geometry of many parts, such as vane segments, this limits the places where fine feature can be formed into the casting, such as the shroud backside surface. The flexible liner inside the rigid core die obviates this problem because the flexible liner is used to form the fine features and the flexible liner can flex around the fine features as it is removed.
The inventors have taken advantage of this flexible liner to create the integral casting core that innovatively forms the cooling channel of the airfoil portion of the vane segment while simultaneously forming the backside surface of the shroud, which was previously formed either by a ceramic shell or a discrete, ceramic insert. Fine features may also be formed on the backside surface using the integral casting core because in this casting method the shroud backside, and hence any shroud backside surface features, are formed directly in the vane segment during casting by the integral core. Since the integral core is forming the fine features there is no concern about loss of the fine features when formed via the wax pattern or misalignment when formed via the discrete, ceramic inserts. Since the flexible liner can be pulled out from around small features that would prevent the separation of rigid core die liners, there is no concern about core die separation.
Due to the geometry of the integral casting core 110, if a rigid core die were used the rigid core die would need to be separated along line 136. However, when the core shell features 130 are configured as shown, where there is a lower elevation 134 between a higher elevation 132 and a nearest point 138 on a surface 142 of the core airfoil portion 116, an interference between the core shell features 130 and the opposite features in the rigid core die would prevent lateral movement between the core shroud portion 118 and the rigid core die. This would necessarily prevent movement along line 136. However, the flexible liner is sufficiently flexible that it can be removed from around the core shell features 130 without causing any damage to them. Any pattern in the core shroud backside-shaping surface 120 that causes an interference that prevents separation of a rigid core die in this manner but which can be formed with the flexible liner 112 is envisioned. One such example would be an array of dimples, or recesses, or trip strips that are not aligned with line 136 etc.
While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only. Numerous variations, changes and substitutions may be made without departing from the invention herein. Accordingly, it is intended that the invention be limited only by-the spirit and scope of the appended claims.
Claims
1. A cast ceramic core, comprising:
- an airfoil portion shaped to define an inner surface of an airfoil of a vane segment; and
- a shell portion comprising a backside-shaping surface shaped to define a backside surface of a shroud of the vane segment, the backside-shaping surface comprising a higher elevation and a lower elevation, the higher elevation being set apart from a nearest point on the airfoil portion by the lower elevation,
- wherein the airfoil portion and the shell portion are cast as a monolithic body during a single casting pour.
2. The cast ceramic core of claim 1, wherein the shell portion defines the backside surface of an outer shroud of the vane segment, and wherein the cast ceramic core further comprises an opposing shell portion comprising an opposing backside-shaping surface shaped to define a backside surface of an inner shroud of the vane segment, the opposing backside-shaping surface comprising the higher elevation and the lower elevation, the higher elevation being set apart from a respective nearest point of the airfoil portion by the lower elevation.
3. A cast ceramic core, comprising an airfoil portion shaped to define an inner surface of an airfoil of a vane segment and a shell portion shaped to define a backside surface of a shroud of the vane segment, wherein the airfoil portion and the shell portion are formed as a single casting.
4. The cast ceramic core of claim 3, wherein the shell portion further comprises core shell features shaped to define heat transfer features on the backside surface of a vane segment shroud.
5. The cast ceramic core of claim 4, wherein the airfoil portion comprises core airfoil features shaped to define heat transfer features on the inner surface of a vane segment airfoil.
6. The cast ceramic core of claim 4, wherein the core shell features form a higher elevation and a lower elevation in the shell portion, the higher elevation being set apart from a nearest point on the airfoil portion.
7. The cast ceramic core of claim 3, wherein the shell portion defines the backside surface of an outer shroud of the vane segment, and wherein the cast ceramic core further comprises an opposing shell portion shaped to define a backside surface of an inner shroud of the vane segment.
8. The cast ceramic core of claim 7, wherein the shell portion further comprises core shell features shaped to define heat transfer features on the backside surface of the outer shroud, wherein the opposing shell portion further comprises core shell features shaped to define heat transfer features on the backside surface of the inner shroud.
9. The cast ceramic core of claim 8, wherein the core shell features on at least one of the shell portions form a higher elevation and a lower elevation in the at least one shell portion, the higher elevation being set apart from a nearest point on the airfoil portion.
10. The cast ceramic core of claim 8, wherein the core shell features on both shell portions comprises a plurality of dimples.
11. A cast ceramic core, comprising:
- a monolithic body comprising: an airfoil portion shaped to define an inner surface of an airfoil of a vane segment; an outer shell portion shaped to define a backside surface of an outer shroud of the vane segment; and an inner shell portion comprising a core backside-shaping surface shaped to define a backside surface of an inner shroud of the vane segment.
12. The cast ceramic core of claim 11, wherein at least one of the core shell portions is further shaped to define a heat transfer feature on a respective backside surface of the vane segment.
13. The cast ceramic core of claim 12, wherein the further shaping forms a higher elevation and a lower elevation in the at least one shell portion, the higher elevation being set apart from a nearest point on the airfoil portion.
14. The cast ceramic core of claim 12, wherein the further shaping forms a plurality of dimples on the respective backside surface.
15. The cast ceramic core of claim 12, wherein both backside-shaping surfaces are further shaped to define heat transfer features on respective backside surfaces of the vane segment, the further shaping forming a higher elevation and a lower elevation in each backside-shaping surface, the higher elevations being set apart from respective nearest point of the airfoil portion.
16. The cast ceramic core of claim 15, wherein the further shaping forms a plurality of dimples.
Type: Application
Filed: Nov 7, 2013
Publication Date: May 7, 2015
Inventors: Ching-Pang Lee (Cincinnati, OH), Gerald L. Hillier (Charlottesville, VA), Jae Y. UM (Winter Garden, FL), Gm Salam Azad (Oviedo, FL)
Application Number: 13/998,541
International Classification: B22C 9/24 (20060101); B22C 9/10 (20060101);