GB2430170A

GB2430170A - Method of forming a turbine nozzle guide vane

Info

Publication number: GB2430170A
Application number: GB0518802A
Authority: GB
Inventors: Mark John Simms; Michael John Beauchamp
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 2005-09-15
Filing date: 2005-09-15
Publication date: 2007-03-21
Anticipated expiration: 2025-09-15
Also published as: US20070059171A1; EP1764171A1; GB0518802D0; GB2430170B

Abstract

A method of forming a turbine nozzle guide vane 2 for a gas turbine engine, the guide vane 2 comprising an internal cavity 14 and having internal features 16, comprises investment casting metal around a core member 30 that defines the internal cavity 14 and internal features 16 of the guide vane, removing the core member 30, and machining the guide vane 2. The process of investment casting around the core member 30 includes the step of casting at least one feature 40 external to the guide vane 2. The external feature 40 is used as a reference point to indicate the location of the internal features 16 of the guide vane 2 during the machining of the guide vane 2.

Description

METHOD OF FORMING A CAST COMPONENT

This invention relates to a method of forming a cast component, especially a turbine nozzle guide vane.

Gas turbine engines use nozzle guide vanes within the turbine section of the engine to direct gas flow onto the turbine blades in the most effective manner. A standard nozzle guide vane includes an aerofoil that extends between an inner and an outer platform.

The aerofoil directs the gas flow between the inner and outer platforms such that each platform has a first, gas washed side and a second, non gas washed side. It is standard practice to cool turbine blades and the aerofoils of nozzle guide vanes in a gas turbine engine. In certain engine applications it is also necessary to cool the platforms of the nozzle guide vanes. Several methods of nozzle guide vane cooling exist and an appropriate method may be selected according to the magnitude of the temperatures experienced in the area to be cooled.

One method of nozzle guide vane platform cooling is illustrated in Figures 2 and 3. The method calls for a double skin platform design, whereby an internal cavity is created in the nozzle guide vane platform between the two skins. Cooling air is fed into the cavity via impingement holes formed on the non gas washed surface of the platform and flows through the cavity to cool the platform. Columns or pedestals extend across the cavity between the two skins in order to allow for load and heat transfer across the platform.

Conventionally, the non gas washed skin of the platform is constructed as a separate component that is pre drilled with impingement holes and attached to the main component to form the double skinned design. This procedure is time consuming and produces an inferior component. Poor joint integrity at the column/skin interface results in reduced load and heat transfer across the platform.

The problem of joint integrity can be addressed by forming the platform cavity during the casting process using a platform core. In this manner the entire component is cast in a single process step and a good connection between the columns and both skins can be achieved. However, the position of the columns within the cavity cannot be detected once the component has been cast. Movement of the platform core during the casting process is not uncommon, so the exact position of the columns within the cavity cannot be determined. There is therefore a risk that, during the subsequent drilling process, an impingement hole could be drilled over the top of a column, rather than between columns, as is intended. This situation is illustrated in Figure 4. Wrongly positioned impingement holes reduce cooling effectiveness and can cause component failure under normal operating conditions.

According to the present invention, there is provided a method of forming a cast component comprising an internal cavity and having internal features, the exact position of which is to be subsequently determined, the method comprising: investment casting metal around a core member that defines the internal cavity and internal features of the component, removing the core member, and performing a machining operation on the component the orientation of which is to be relative to the internal cavity, characterised in that the core member includes at least one part thereof which in the process of casting produces at least one externally accessible feature in the cast component, and in that the at leasxternally accessible feature is used as a reference to indicate the location of the internal features of the component so as to determine the required orientation of the machining operation.

In such a method, any movement of the core member during casting is reflected in the position of the external feature(s). It is an advantage of the invention that the external feature(s) reflects the location of the internal features of the guide vane, allowing machining of the guide vane to take place accurately with respect to the position of the internal features. It is a further advantage of the invention that casting of the external feature does not require an additional process step.

The external reference feature is preferably cast using an aperture through a portion of the core member that extends outside the guide vane. Consequently, the external reference feature is a protrusion. However the feature may take any appropriate form.

For example, the reference feature may be in the form of a recess.

Preferably, the process of investment casting around the core member includes the step of casting three external reference features. Preferably, the external feature or features define three separate faces which lie in mutually perpendicular planes, so that the position of the core can be determined precisely in three dimensional space. Each external feature may be cast adjacent to a specific area of the cavity so as to correspond to specific internal features.

The guide vane may comprise a guide vane platform in which the internal cavity is provided, the guide vane platform having a first skin and a second skin disposed on either side of the cavity. The guide vane platform may be an inner or an outer platform.

The internal features of the guide vane may comprise columns that extend across the internal cavity to connect the first and second skins.

Machining the guide vane may comprise forming at least one hole through one of the first and second skins to intersect the internal cavity at a predetermined location, the desired position of the hole being established by reference to the external feature. The hole may be an impingement hole and may be one of a plurality of holes located across the guide vane skin.

The external feature may be removed after the guide vane has been machined. This removal may be accomplished as part of the normal fabrication process, for example during sealing of the exit slot created during removal of the core member.

According to another aspect of the present invention, there is provided a turbine nozzle guide vane for a gas turbine engine, the nozzle guide vane comprising an internal cavity, internal features and at least one external feature, characterised in that the internal and external features are formed by a common core component whereby the position of the external feature is indicative of the position of the internal features.

For a better understanding of the present invention, and to show more clearly how it may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which: Figure 1 is a perspective view of a turbine nozzle guide vane; and Figure 2 is a partial sectional view of an outer nozzle guide vane platform; and Figure 3 is a partial sectional view of the nozzle guide vane platform of Figure 1 indicating cooling air flow; and Figure 4 is a partial sectional view of an outer nozzle guide vane platform illustrating core movement during casting; and Figure 5 is a perspective view of the core component with the outline of the resulting nozzle guide vane platform shown behind; and Figure 6 is a perspective view of a nozzle guide vane platform.

Referring to Figure 1, a turbine nozzle guide vane 2 comprises an aerofoil 4 that extends between inner and outer platforms 6, 8. In use, hot combustion gas flows across the guide vane 2, between the inner and outer platforms 6, 8 and is directed by the aerofoil 4 into the path of turbine blades (not shown). The surfaces of the platforms 6, 8 that are adjacent to the aerofoil are washed by the passing gas stream.

Referring to Figures 2 to 4, the outer nozzle guide vane platform 8 comprises first and second skins 10, 12 that are disposed on opposite sides of a cavity 14. The first skin forms the gas washed surface of the platform 8 and the second skin 12 forms the non gas washed surface of the platform 8. Impingement holes 18 extend through the skin 12 into the cavity 14, such that the non gas washed surface of the platform 8 communicates with the interior of the cavity 14. Columns 16 extend across the cavity 14, connecting the first and second skins 10, 12.

Referring to Figure 1, the structure of the inner nozzle guide vane platform 6 is complementary to that of the outer nozzle guide vane platform 8. The inner platform 6 comprises first and second skins 20 and 22 disposed on opposite sides of a cavity (not shown). Impingement holes (not shown) extend through the second skin 22 into the cavity, and columns (not shown) extend across the cavity connecting the first and second skins 20, 22.

The nozzle guide vane platforms 6, 8 are constructed using an investment casting process. During this process, a ceramic core member is placed in a die into which wax is injected. The ceramic cored wax model is then repeatedly dipped into a slurry and invested with ceramic particles. When the outer ceramic coating is dry, the model is fired in an oven to remove the wax and harden the ceramic material. The resulting cored shell is then used as a mould to cast the hollow guide vane platforms 6, 8 in metal. When the metal platform has cooled, the outer ceramic investment shell and inner core are removed. Impingement holes are then drilled through a skin of the platform to communicate with the cavity formed by the inner core.

An inner platform core 30 is illustrated in Figure 5, with the outline of the resulting inner platform 6 indicated behind the core. The core 30 comprises a central region 34, which remains within the platform 6 during casting, and two side regions 36, which extend beyond the platform 6 during casting. The central region 34 of the core 30 includes a series of apertures 32 through which molten metal flows during the casting process to form the columns 16 within the cavity 14. The core 30 also includes three larger apertures 38, which are located on the boundary between the central and outer regions 34, 36 of the core 30. Molten metal flows through the apertures 38 to create three protrusions 40 on the sides of the platform 6, as illustrated in Figure 6.

The protrusions 40 on the edges of the platform 6 are formed at the same time as the columns 16. The position of the protrusions 40 is fixed with respect to that of the columns 16. Protrusions 40 are therefore used as reference members to indicate the position of the columns 16 within the cavity 14 during subsequent machining of the platform 6. Any deviation of the columns 16 from their intended position, caused by movement of the core 30 during the casting process, will be reflected by a similar deviation in the position of the protrusions 40 from their intended position.

The platform 6 is mounted on drilling apparatus in order to drill the impingement holes 18 through the skin 12. The platform 6 is located on the drilling apparatus using only the protrusions 40 so that the drilling operation is conducted relative to the position of the internal columns 16 and not the external surfaces of the plafform 6.

When the drilling operation is complete, the exit slots left by the removal of the core 30 are sealed by weld closure, brazing or any other appropriate measure. During this procedure, if required, the protrusions 40 may be removed from the platform 6.

Claims

A method of forming a cast component comprising an internal cavity and having internal features the exact position of which is to be subsequently determined, the method comprising: investment casting metal around a core member that defines the internal cavity and internal features of the component, removing the core member, and performing a machining operation on the component the orientation of which is to be relative to the internal cavity, characterised in that the core member includes at least one part thereof which in the process of casting produces at least one externally accessible feature in the cast component, and in that the at leastexternally accessible feature is used as a reference to indicate the location of the internal features of the component so as to determine the required orientation of the machining operation.
2 A method as claimed in claim 1, wherein the externally accessible feature is cast using an aperture that passes through a portion of the core member that extends outside the guide vane.
3 A method as claimed in claim I or 2, wherein the externally accessible feature is a protrusion.
4 A method as claimed in any one of the preceding claims wherein the process of investment casting around the core member includes the step of casting three external features.
A method as claimed in any one of the preceding claims wherein the external feature or features define three separate faces which lie in mutually perpendicular planes.
6 A method as claimed in claim 5 wherein the three separate faces are spaced apart.
7 A method as claimed in any one of the preceding claims wherein the guide vane comprises a guide vane platform in which the internal cavity is provided, the guide vane platform having a first skin and a second skin disposed on either side of the cavity.
8 A method as claimed in claim 7, wherein the internal features of the guide vane comprise columns that extend across the internal cavity to connect the first and second skins.
9 A method as claimed in claim 7 or 8, wherein machining the guide vane comprises forming at least one hole through one of the first and second skins, the desired position of the hole being established by reference to the external feature.
A method as claimed in any one of the preceding claims, further comprising removing the external feature after the guide vane has been machined.
11 For use in the method of any of the preceding claims a core member for defining the internal cavity of the cast component provided with at least one part thereof which in the process of casting produces at least one externally accessible feature in the cast component.
12 An internally cooled aerofoil for a gas turbine engine, the aerofoil having internal cooling passages, internal features and at least one external feature, characterised in that the cooling passages, internal features and external features are formed by a common core component whereby the position of the at least one external feature is indicative of the position of the internal features.