US20020029863A1

US20020029863A1 - Method for producing a cooled, lost-wax cast part

Info

Publication number: US20020029863A1
Application number: US09/921,587
Authority: US
Inventors: Gordon Anderson; Peter Marx; Shailendra Naik
Original assignee: Individual
Current assignee: Ansaldo Energia IP UK Ltd
Priority date: 2000-08-07
Filing date: 2001-08-06
Publication date: 2002-03-14
Anticipated expiration: 2021-08-06
Also published as: DE10038453A1; EP1193006A2; US6435256B1; EP1193006B1; DE50107262D1; EP1193006A3

Abstract

The invention relates to a method for producing a cooled cast part (1) for a thermal turbo machine by using a known casting process. Between a wax model (10) of the cast part (1) and a ceramic core (6), a wax seal (8) is applied by hand above a step (7), only on an additional shoulder (9). The material that is created during the casting process at this point by the shoulder (9) and the wax seal (8) can be ground off without causing rough areas on the step (7) to form. This simplifies the welding or soldering of a cooling plate to the step (7).

Description

FIELD OF THE INVENTION

The invention relates to a method for producing a cooled cast part produced by a lost-wax process for a thermal turbo machine according to the preamble of

claim

1.

BACKGROUND OF THE INVENTION

Cast parts for thermal turbo machines are produced using known casting processes. Casting furnaces for such casting processes are known, for example, from publications EP-A1-749 790, U.S. Pat. No. 3,763,926, or U.S. Pat. No. 3,690,367. The casting molds usually are provided in the form of a wax model. A process for producing a complex part of a gas turbine using a casting mold is known, for example, from publication U.S. Pat. No. 5,296,308.

Depending on the specific embodiment, a core is placed into the wax model. This core contains the structure of the cavity that forms a specific cooling structure inside the casting part. In these casting parts, a wax seal must be applied between the wax model and the core in order to prevent the slip, that in its dry form forms the casting mold, from penetrating into the intermediate space. The wax seal is applied by hand onto a step adjoining the core. This step has the ultimate purpose of holding a cooling plate. The cooling plate is soldered or welded onto the step and is used, by means of cooling holes, for impact-cooling the platform located below it. In order to prevent leakages of cooling air, the surface of this step should be smooth. But this is in contradiction with the applied wax seal that, after casting, results in an accumulation of material above the step. In order to get closer to the goal of a smooth surface of the step, an additional process step, for example grinding or eroding, is necessary.

SUMMARY OF THE INVENTION

The invention is based on the objective of creating a method for producing a thermally loaded and cooled cast part for a thermal turbo machine by using a known casting process, whereby the casting mold of the cast part is produced with a wax model and a ceramic core, and the subsequent production steps are simplified and optimized.

According to the invention, this objective is realized with a method according to the preamble of Claim 1 in that, prior to the production of the casting mold of the cast part between the wax model and the core, the wax seal is applied to only one shoulder that is located above the step in the direction towards the side of the core.

This provides the advantage that even during the casting process it can already be prevented that rough areas are created on the step that would result in a leakage of the cooling air at the cooling plate. The material that is created during the casting process as a result of the wax seal and the shoulder can be ground off or removed using another appropriate manner with a uniform process step without forming rough areas on the step. A cooling plate can be soldered to this step without any additional process steps.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention is described in reference to the enclosed drawings, whereby [0007]
FIG. 1 shows a model of a turbine blade, [0008]
FIG. 2 shows a section through a turbine blade according to the invention along to line II-II in FIG. 1, and [0009]
FIG. 3 shows a section through a turbine blade according to the invention along line II-II in FIG. 1 after a successful casting process.[0010]
Only those elements essential to the invention are shown. Identical elements are designated with the same reference characters in the different drawings. [0011]

DETAILED DESCRIPTION OF THE INVENTION

The invention relates to a method for producing a thermally loaded and cooled lost-wax cast part for a thermal turbo machine. In particular, this may be, for example, a guide or rotating blade, or other cooled rotor or stator segments of a gas turbine or compressor. These cast parts and the method according to the invention for their production are explained in more detail below in reference to the enclosed figures. [0012]
The cast parts are produced using casting furnaces known generally from the state of the art. By using such casting furnaces, complex components that can be subjected to high thermal and mechanical loads can be created. Depending on the process conditions, it is hereby possible to produce the cast body in a directionally solidified manner. It can hereby be constructed as a single crystal (SX) or polycrystalline, as fringe crystals that have a preferred direction (“directionally solidified”, DS). It is especially important that the directional solidification takes place under conditions at which an intensive heat-exchange takes place between a cooled part of a casting mold holding a molten starting material and the still molten starting material. This permits the formation of a zone of directionally solidified material with a solidification front that, when the heat is continuously withdrawn, migrates through the casting mold while forming the directionally solidified cast part. [0013]
Publication EP-A1-749 790, for example, discloses such a process and apparatus for producing a directionally solidified cast part. The apparatus comprises a vacuum chamber that contains an upper heating chamber and a lower cooling chamber. The two chambers are separated from each other by a baffle. The vacuum chamber accepts a casting mold that is filled with a molten mass. In order to produce thermally and mechanically loadable parts, such as guide or rotating blades for gas turbines, a super-alloy based on nickel can be used, for example. The baffle is provided in the center with an opening through which the casting mold is moved slowly during the process from the heating chamber to the cooling chamber, so that the cast part directionally solidifies from the top to the bottom. The downward movement is brought about with a drive rod on which the casting mold is positioned. The bottom of the casting mold is constructed with water cooling. Below the baffle, means for generating and guiding a gas stream are provided. Through the gas stream next to the lower cooling chamber, these means ensure additional cooling and therefore a greater temperature gradient at the solidification front. [0014]
A similar process, which in addition to the heating and cooling chamber works with an additional gas cooler, is also known, for example, from U.S. Pat. No. 3,690,367. [0015]
Another process for producing a directionally solidified cast part is known from publication U.S. Pat. No. 3,763,926. In this process, a casting mold filled with a molten alloy is immersed continuously into a bath heated to approximately 260° C. This achieves a particularly rapid removal of heat from the casting mold. This and other, similar processes are known under the name of LMC (liquid metal cooling). [0016]
For the invention, it is advantageous, that this type of casting furnaces is used for producing monocrystalline or directionally solidified cast parts, but it is not limited to this. In principle, the solidification also can take place non-directionally. [0017]
FIG. 1 shows a [0018] wax model 10 of a cast part 1, for example a turbine blade to be cast. The turbine blade is provided with a platform 2, a blade vane 3, and blade tip 2. This wax model 10 then is immersed into a liquid, ceramic material, also called a slip. Hereby the later casting mold of cast part 1 is formed around the wax model 10. The ceramic model is then dried so that the casting mold with which the cast part 1 is produced is created. After the slip is dried, the wax is removed using a suitable heat treatment, i.e. is burnt away. During the process step, the casting mold is also fired, i.e. it receives its strength in this way. The cast part 1 is produced in a known manner with the casting mold created in this way by using a known casting furnace that was described in more detail above. The ceramic casting mold and the core are later removed in an appropriate manner, for example by using a strong acid or base.
The turbine blade of FIG. 1 has a cavity into which cooling air is passed during the operation of the turbo machine. This cooling air is able to leave the finished turbine blade again through cooling holes [0019] 5. As seen in FIG. 1, a ceramic core 6 that reflects the internal geometry of the cavity is provided during the production process of the casting mold in the later cavity of the wax model 10. In the shown turbine blade, the platform 2 is cooled additionally by impact cooling. Hereby a cooling plate 11 provided with cooling holes 12 is soldered or welded to a step 7 next to the ceramic core 6 and on the edge of the platform 2 in this cast component. This cooling plate 11 is described in more detail in reference to FIG. 3.
Prior to the production of the casting mold, a [0020] wax seal 8 is manually provided between the ceramic core 6 and shoulder 9. This wax seal 8 has the objective of preventing the undesired penetration of slip into the inner chamber of the ceramic core 6.
FIG. 2 shows a section along line II-II of FIG. 1 that extends through the [0021] step 7, the wax seal 8, and through the ceramic core 6. According to the invention, the wax seal 8 is provided only on a shoulder 9 located above the step 7 towards the ceramic core 6. This process results in two advantages. During the casting process, the step 7 and wax seal 8 create additional, cast material on the turbine blade. As seen in FIG. 3, this material has a specific height s and can be machined, i.e. ground off, independently from step 7 or independently from the surface of step 7. This uniform process step also may be performed by erosion. In spite of this additional process step, the step 7 to which the cooling plate 11 is soldered remains unaffected, which in any case ensures a smooth surface of the step 7. The cooling air 13 penetrates through the cooling holes 12 and in this way is able to cool the platform 2 by impact cooling. The smooth surface of the step 7 is important since even small rough areas could reduce the cooling effect of this impact cooling as a result of leakage losses. Another advantage is that the existing shoulder 9 prevents the liquid solder that distributes itself over the entire step 7 from flowing into the cavity of the cast part 1. Since during the operation of the cast part an insert will be located in its cavity also, it is important that no solder adheres to this insert and thus adversely affects its proper function.

Claims

What is claimed is:

1. Method for producing a cooled cast part (1) for a thermal turbo machine by using a known casting process, whereby the cooled cast part (1) is produced by means of a casting mold, whereby this casting mold is produced by using a wax model (10) and a core (6) located inside the wax model (10), hereby immediately next to the core (6) is located a step (7) for the attachment of a cooling plate (11) to the finished cast part (1), and whereby prior to the production of the casting mold a wax seal (8) is applied by hand between the core (6) and the wax model (10), characterized in that

prior to the production of the casting mold of the cast part (1) between the wax model (10) and the core (6), the wax seal (8) is applied only to a shoulder (9) that is located above the step (7) in the direction towards the side of the core (6).

2. Method as claimed in claim 1, characterized in that

after the casting process, the material on the cast part (1) that is located at the point of the shoulder (9) and the wax seal (8) is partially ground off or eroded, whereby the step (7) is not affected by this process step.

3. Method as claimed in claim 2, characterized in that

the cooling plate (11), in which cooling holes (12) are located, is solder or welded to the surface of the step (7).

4. Method as claimed in one of the previous claims, characterized in that

a casting process for producing monocrystalline, directionally or non-directionally solidified is used.

5. Method as claimed in one of previous claims, characterized in that

it is a method for producing a guide or rotating blade of a gas turbine or a compressor with impact cooling of the platform (2).