GB2571549A

GB2571549A - A core for an investment casting process

Info

Publication number: GB2571549A
Application number: GB1803325.8A
Authority: GB
Inventors: Mottram Martin
Original assignee: Rolls Royce PLC
Current assignee: Rolls Royce PLC
Priority date: 2018-03-01
Filing date: 2018-03-01
Publication date: 2019-09-04
Also published as: GB201803325D0; US20190270131A1

Abstract

A core 300 for use in an investment casting process comprises first and second portions 302 & 301 which lie at an angle to each other. The second core portion 301 connects with the first core portion 302 at an intermediate location between the ends 303 & 304 of the first core portion 302 and comprises at least one indent, groove or recess 306 that extends perpendicularly to its length and is located close to the first core portion. A ceramic shell mould for investment casting comprises the above core 300 surrounded by a layer of sacrificial wax and a ceramic shell, with the second core portion 301 extending to the ceramic shell through the sacrificial wax. The core 300 can be used to make a seal segment for bounding a portion of a main gas path in a gas turbine engine or a combustion tile. The core indent, groove or recess 306 forms a similar feature in a cooling passage which generates impingement cooling enhancement at that point in the cast component.

Description

The present disclosure relates to an investment casting core for a component having one or more internal passages which require high precision positioning.

Figure 1 shows a ducted fan gas turbine engine 10 comprising, in axial flow series: an air intake 12, a propulsive fan 14 having a plurality of fan blades 16, an intermediatepressure compressor 18, a high-pressure compressor 20, a combustor 22, a highpressure turbine 24, an intermediate-pressure turbine 26, a low-pressure turbine 28 and a core exhaust nozzle 30. The fan, compressors and turbines are all rotatable about a principal axis 31 of the engine 10. A nacelle 32 generally surrounds the engine 10 and defines the intake 12, a bypass duct 34 and a bypass exhaust nozzle 36.

Air entering the intake 12 is accelerated by the fan 14 to produce a bypass flow and a core flow. The bypass flow travels down the bypass duct 34 and exits the bypass exhaust nozzle 36 to provide the majority of the propulsive thrust produced by the engine 10. The core flow enters in axial flow series the intermediate-pressure compressor 18, high-pressure compressor 20 and the combustor 22, where fuel is added to the compressed air and the mixture burnt. The hot combustion products expand through and drive the high-, intermediate- and low-pressure turbines 24, 26, 28 before being exhausted through the nozzle 30 to provide additional propulsive thrust. The high-, intermediate- and low-pressure turbines 24, 26, 28 respectively drive the high- and intermediate-pressure compressors 20, 18 and the fan 14 by interconnecting shafts 38, 40, 42.

The performance of gas turbine engines, whether measured in terms of efficiency or specific output, is generally improved by increasing the turbine gas temperature. It is therefore desirable to operate the turbines at the highest possible temperatures. As a result, the turbines in state of the art engines, particularly high-pressure turbines, operate at temperatures which are greater than the melting point of the material of the blades and vanes making some form cooling necessary.

Typically, components are cooled by a flow of compressed air which is at a higher pressure than the main gas path but a significantly lower temperature. Components are provided with internal cooling passages which both distribute the cooling air and act to internally cool a particular component.

A continuing challenge of providing cooling passages within components is to improve the tolerance with which the passages can be placed within components so that the wall thickness of a component can be reduced so far as possible.

Typically, cooling passages can be provided by so-called lost wax method or investment casting of components as is well known in the art of casting technology. Lost wax casting involves the principal steps of forming a ceramic core, surrounding the core with a wax (or other suitable sacrificial material), prior to coating the waxed core with a ceramic shell. The core defines an internal cavity within the cast metal component, the wax defines the space in which metal will be cast, and the shell defines the external surface of the cast metal component.

The core may be injection moulded prior to consolidation by drying and optionally firing. The core is then placed in a second mould and wax is injected. The wax covered core is then repeatedly dipped in ceramic slurry to provide the shell. Once the shell is dry, the wax is removed using the appropriate process as defined by the chemistry of the wax (e.g. by soaking in water for a water soluble wax, or heating) and the vacated mould fired to ready it for receiving molten metal. To cast the object, metal is poured into the cavity which has been provided by the removed wax. After the metal has solidified, the ceramic parts are removed by a leaching process to leave the cast metal component which may be further processed by machining or annealing for example.

EP3064290A1 describes a core for an investment casting process, comprising: a core passage which extends between a first point and a second point along a tortuous path having length L, wherein the first point and second point are separated by a direct line of sight distance, S, wherein L is greater than S; and, a core bridge which extends between the first and second points away from the core passage.

The disclosure seeks to provide an improved core structure and method of casting a component which allows for the manufacture of improved components with enhanced cooling properties.

According to a first aspect there is provided a core for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core, the core comprising: a chimney portion; and a core passage, the chimney portion extending away from the core passage; wherein the chimney portion comprises at least one indent, groove or recess.

The chimney portion may be perpendicular to the core passage. The chimney portion may extend away from the core passage in a non-perpendicular direction, e.g. at an angle of up to 30°, up to 20°, up to 10° or up to 5° from the perpendicular direction. The chimney portion may extend away from the core passage at an angle of at least 1° or at least 3° from the perpendicular.

The core passage may extend from a first end to a second end. The first end may be an upstream end and the second end may be a downstream end.

The chimney portion may connect with the core passage at an intermediate location between the first end and the second end.

A base of the core passage may extend from the first end to the second end.

The core passage may be considered generally planar. The chimney portion can thus be thought of as extending out of a plane defined at least in part by the core passage. It will be appreciated that the plane may be a circumferential plane in the example of the cast component being a seal segment for use in a gas turbine engine, due to the seal segment forming part of an annular wall. Hence, the plane may be curved.

The chimney portion and the core passage each form an internal passageway in the cast component. The formed internal passageways may communicate with each other to provide a continuous internal passageway. The continuous internal passageway may extend from an inlet corresponding to at least a portion of an end of the chimney portion distal from the core passage to an outlet corresponding to at least a portion of the downstream end of the core passage. In a cast component manufactured using the core, one or more holes, e.g. machined holes, through an exterior wall of the component may communicate with the outlet corresponding to at least a portion of the downstream end of the core passage.

The indent, groove or recess may extend in a transverse direction across the chimney portion. The indent, groove or recess may be disposed relatively close to the core passage. The indent, groove or recess may be disposed within 10 cm, within 5 cm or within 1 cm of the core passage.

A second aspect provides a ceramic shell for an investment casting process in which a component to be cast has at least one internal passageway, the internal passageway(s) being provided by a core, the ceramic shell comprising: a core according to the first aspect, the core having an outer layer of a sacrificial material within the ceramic shell, wherein the chimney portion extends between the core passage and the ceramic shell through the sacrificial material.

The component to be cast may have at least one exterior wall.

The sacrificial material may be wax-based.

A third aspect provides a cast component comprising: at least one internal passageway formed by a core of the second aspect, wherein the internal passageway has a local area contraction corresponding to the indent, groove or recess.

The cast component may comprise one or more further caps sealing apertures at one or more further points.

The cast component may be a seal segment for bounding a portion of a main gas path of a gas turbine engine. The cast component may be a combustion tile.

A fourth aspect provides a gas turbine engine comprising a cast component of the third aspect.

A method for casting a component may comprise: providing a ceramic shell as described above; removing the sacrificial material; pouring molten metal into a cavity created by the removal of the sacrificial material.

The molten metal may comprise, or consist essentially of, an alloy such as a nickel alloy or an aluminium alloy. In a cast component manufactured using the method, the metal may be present as a single crystal.

The core may be injection moulded from a ceramic material prior to solidification and drying. The method may further comprise removing the ceramic shell and core, wherein the first point is provided as an inlet for the passageway within the component and the second point is sealed over with a cap.

The skilled person will appreciate that except where mutually exclusive, a feature described in relation to any one of the above aspects may be applied mutatis mutandis to any other aspect. Furthermore except where mutually exclusive any feature described herein may be applied to any aspect and/or combined with any other feature described herein.

Embodiments will now be described by way of example only, with reference to the Figures, in which:

Figure 1 is a sectional side view of a gas turbine engine;

Figure 2 shows a cross section of a turbine shroud arrangement;

Figure 3 is a side view of a core for use in casting a component containing one or more internal passageways.

Figure 4 is a perspective view of another core for use in casting a component containing one or more internal passageways;

Figure 5 is a plan view of the core shown in Figure 4;

Figure 6 is an end elevation of the core shown in Figure 4 and Figure 5; and Figure 7 shows a cast component.

Figure 2 provides a cross-section of a shroud arrangement 210 and surrounding structure which can be located within the architecture of a substantially conventional gas turbine engine, e.g. as illustrated in Figure 1. Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. By way of example such engines may have an alternative number of interconnecting shafts (e.g. two) and/or an alternative number of compressors and/or turbines. Further the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.

The shroud arrangement 210 forms part of the turbine section of a gas turbine engine similar to that shown in Figure 1 and defines the boundary of the hot gas flow path 211 thereby helping to prevent gas leakage and provide thermal shielding for the outboard structures of the turbine.

The turbine (rotor) blade 212 sits radially inwards of the shroud arrangement 210 and is one of a plurality of conventional radially extending blades which are arranged circumferentially around a supporting disc (not shown) which is rotatable about the principal axis 31 (Figure 1) of the engine. Corresponding arrays of nozzle guide vanes 214a, 214b, are axially offset from the rotor blades 212 with respect to the principal axis 31 (Figure 1) of the engine 10 (Figure 1) and alter the direction of the upstream gas flow such that it is incident on the rotor blades 212 at an optimum angle. Thus, the turbine generally consists of an axial series of nozzle guide vanes 214a and rotor blade 212 pairs arranged along the gas flow path 211 of the turbine, with different pairs being associated with each of the high pressure turbine (HPT), intermediate pressure turbine (IPT) and low pressure turbine (LPT). A given turbine may have more than one nozzle guide vane and rotor blade pairs associated therewith.

The shroud arrangement 210 shown in Figure 2 principally includes three main parts: a seal segment 216, a carrier segment 218 and an engine casing 220 which sit in radial series outside of the main gas path 211 and rotor blade 212. The shroud arrangement 210 of the embodiment is that of an high pressure turbine, but the disclosure may be applied to other areas of the turbine, or indeed other non-turbine applications where appropriate.

The seal segment 216 includes a plate 222 having an inboard gas path facing surface 224 and an outboard surface 226 which is provided by the radially outward surfaces of the plate 222 relative to the principal axis 31 of the engine 10. The seal segment 216 is one of an array of similar segments which are linked so as to provide an annular shroud which resides immediately radially outwards of the turbine rotor blades 212 and defines the radially outer wall of the main gas flow path 211. Thus, the seal segment 216 shown is one of a plurality of similar arcuate segments which circumferentially abut one another to provide a substantially continuous protective structure around the rotor blade 212 tip path.

The seal segment 216 is fixed to the engine casing 220 via a corresponding carrier segment 218. The carrier segment 218 is one of a plurality of segments which join end to end circumferentially to provide an annular structure which is coaxial with the principal axis 31 of the engine. The engine casing 220 is a full annular housing which sits outboard of the carrier 218 and generally provides structural support and containment for the turbine components, including providing direct support for the shroud cassette which comprises the seal segment and carrier 218.

The seal segment 216 is contacted by the hot gas flow through the turbine and thus requires cooling fluid, e.g. air. The choice of cooling fluid, e.g. air, source is largely dictated by the required reduction in temperature at a particular location and the expected working pressure the cooling fluid, e.g. air, exhausts into.

The cooling fluid, e.g. air, can be provided from any suitable source. The cooling fluid, e.g. air, may be provided in the form of bleed air from one or more compressor stages. Thus, air may be bled from the compressor and passed through various air cooling circuits both internally and externally of the components to provide the desired level of cooling.

To provide suitable cooling to the seal segment, internal passageways are provided in the plate 222 which channel cooling fluid, e.g. air, through the component prior to being exhausted ultimately into the main gas path.

Figure 3 is a side view of a core 300 for use in casting a component containing one or more internal passageways. The component may comprise a seal segment or a combustion tile for use in a gas turbine engine. The core 300 provides the internal passageway(s) of the cast component.

Very generally, the core 300 is moulded from a ceramic material which is subsequently coated in wax prior to being encased in a ceramic shell. The wax is then removed and molten metal poured into the ceramic shell and the vacancy left by the wax. The core 300 and shell are then removed to provide a hollow metal cast part with an internal passageway (or passageways) corresponding to the shape of the core 300.

The core 300 comprises a chimney portion 301 and a core passage 302. The chimney portion 301 extends away from the core passage 302. The chimney portion 301 is perpendicular to the core passage 302. The chimney portion 301 extends away from the core passage 302 such that it can pass through the sacrificial layer, e.g. wax, once applied, and connect with the ceramic shell. In so doing, the chimney portion 301 extends away from the core passage 302 through an exterior wall of the component once cast, so as to leave a hole in an exterior-facing surface. The chimney portion 301 serves to hold the core 300 in the correct position during the casting process.

The core passage 302 extends from an upstream end 303 to a downstream end 304. The chimney portion 301 connects with the core passage 302 at an intermediate location between the upstream end 303 and the downstream end 304. A base 307 of the core passage 302 extends from the upstream end 303 to the downstream end 304.

The core passage 302 may be considered generally planar. The chimney portion 301 can thus be thought of as extending out of a plane defined at least in part by the core passage 302. It will be appreciated that the plane may be a circumferential plane in the example of the cast component being a seal segment for use in a gas turbine engine, due to the seal segment forming part of an annular wall. Hence, the plane may be curved. Thus, the chimney portion 301 may extend out relative to the tangential plane in the immediate vicinity of the point at which it connects with the core passage 302. However, it will also be appreciated that a core passage may extend along a curved or stepped path having different radii of curvature and relative height levels, in which a satisfactory definition of a plane cannot be obtained.

The chimney portion 301 and the core passage 302 each form an internal passageway in the cast component. The formed internal passageways communicate with each other to provide a continuous internal passageway from an inlet corresponding to at least a portion of an end 306 of the chimney portion 301 distal from the core passage 302 to an outlet corresponding to at least a portion of the downstream end 304 of the core passage 302.

The chimney portion 301 comprises a groove 306, which extends in a transverse direction across the chimney portion 301. The groove 306 is disposed relatively close to the core passage 302. The groove 306 provides a local area contraction in the passageway in the cast component. The local area contraction acts to generate an impingement cooling enhancement, as cooling fluid, e.g. air, passes along the internal passageway from the inlet to the outlet. The local area contraction causes an increase in the pressure of the cooling fluid, which then accelerates as it exits the local area contraction. The accelerated cooling fluid impinges on a hot surface of the cast component corresponding to the base 307 of the cooling passage 302. The accelerated cooling fluid has increased momentum, thereby enhancing the impingement cooling. The chimney portion may comprise more than one groove, e.g. a pair of grooves on opposite sides of the chimney portion. It will be appreciated that the groove is simply an example of a suitable feature for providing a local area contraction. One or more other features that provide a local area contraction such as indents or recesses may be present instead of or as well as a groove.

Figures 4, 5 and 6 show another example of a core 400 for use in casting a component containing one or more internal passageways. The component may comprise a seal segment or a combustion tile for use in a gas turbine engine. The core 400 provides the internal passageway(s) of the cast component.

Very generally, the core 400 is moulded from a ceramic material which is subsequently coated in wax prior to being encased in a ceramic shell. The wax is then removed and molten metal poured into the ceramic shell and the vacancy left by the wax. The core 400 and shell are then removed to provide a hollow metal cast part with an internal passageway (or passageways) corresponding to the shape of the core 400.

The core 400 comprises a core passage 401. The core passage 401 has an upstream end 402 and a downstream end 403.

The core passage 401 may be considered generally planar. It will be appreciated that the plane may be a circumferential plane in the example of the cast component being a seal segment for use in a gas turbine engine, due to the seal segment forming part of an annular wall. Hence, the plane may be curved. However, it will also be appreciated that a core passage may extend along a curved or stepped path having different radii of curvature and relative height levels, in which a satisfactory definition of a plane cannot be obtained.

Within the core passage 401, a first cooling passage 404 includes a first point 405 and a second point 406 and has a tortuous path 420 between the first point 405 and the second point 406. The first point 405 and the second point 406 are separated by a direct line of sight distance S and tortuous path 420 has a length L. L is greater than S.

The core 400 comprises a first core bridge 421a extending away from the core passage 401. The first core bridge 421a comprises a first pillar 422, a second pillar 412a and a bridge portion 423a extending between the first pillar 422 and the second pillar 412a. The first pillar 422 comprises a core inlet portion 408. The core inlet portion 408 has a height H1 at the first point 405. The second pillar 412a has a height H2 at the second point 406. H1 is less than H2.

The first point 405 may be considered to be at any point in the core passage 401 underneath the first pillar 422 and/or the core inlet portion 408. The second point 406 may be considered to be at any point in the core passage 401 underneath the second pillar 412a. Wherever the first point 405 and the second point 406 are located, there is no straight path within the core passage 401 from the first point 405 to the second point 406. The direct line of sight distance S will be at least as long as the bridge portion 423a.

The first core bridge 421a comprises a transition region 410a. The transition region 410a has a curved upper surface 411a. The curved upper surface 411a connects an upper surface 409 of the core inlet portion 408 to an upper surface 414a of the second pillar 412a.

The second pillar 412a is thicker than the core inlet portion 408. The transition region 410a includes a pair of transition region side walls 413a, 413a'. The transition region side walls 413a, 413a' are disposed on opposite sides of the first core bridge 421a. The transition region side walls 413a, 413a' each connect a side wall of the first pillar 422 to a side wall of the second pillar 412a.

The first core bridge 421a comprises a shell lock feature 415a. The shell lock feature 415a has the form of a groove. The shell lock feature 415a extends partially across a side wall of the second pillar 412a. The shell lock feature 415a may be machined into the core 400.

The core 400 further comprises a second core bridge 421b extending away from the core passage 401. The second core bridge 421b comprises the first pillar 422, which the second core bridge 421b shares with the first core bridge 421a, a second pillar 412b and a bridge portion 423b extending between the first pillar 422 and the second pillar 412a. The second pillar 412b is taller than the first pillar 422.

The second core bridge 421b comprises a transition region 410b. The transition region 410b has a curved upper surface 411b. The curved upper surface 411b connects the upper surface 409 of the core inlet portion 408 to an upper surface 414b of the second pillar 412b.

The second pillar 412b is thicker than the core inlet portion 408. The transition region 410b includes a pair of transition region side walls 413b, 413b'. The transition region side walls 413b, 413b' are disposed on opposite sides of the second core bridge 421b. The transition region side walls 413a, 413a' each connect a side wall of the first pillar 422 to a side wall of the second pillar 412a.

The second core bridge 421b comprises a shell lock feature 415b. The shell lock feature 415b has the form of a groove. The shell lock feature 415b extends partially across a side wall of the second pillar 412b. The shell lock feature 415b may be machined into the core 400.

The first core bridge 421a and the second core bridge 421b can be thought of as extending out of the plane defined by the core passage 401.

The second pillars 412a, 412b extend away from the core passage 401 such that they can each pass through the sacrificial layer, e.g. wax, once applied, and connect with the ceramic shell. In so doing, the second pillars 412a, 412b extend away from the core passage, through the component wall once cast, so as to each leave a hole in an exterior facing surface. The core inlet portion 408 also leaves a hole in the exterior facing surface. The hole left by the core inlet portion 408 is less thick than the holes left by the second pillars 412a, 412b.

It will be appreciated that the relative position of the first and second points with respect to the length of the first cooling passage and/or the core passage, and the span of the or each core bridge, may vary.

It will be appreciated that other configurations of core bridge(s) may be possible. For example, the core may comprise any number of core bridges. Similarly, one or more of the core bridges may not share a common pillar with one or more other core bridges. The first pillar and/or the second pillar of the or each core bridge may generally be polygonal in transverse cross-section, e.g. rectangular. Alternatively, the first pillar and/or the second pillar of the or each core bridge may be curved at least in part in transverse cross-section.

The core inlet portion may comprise at least one indent, groove or recess. The or each indent, groove or recess may extend in a transverse direction at least partially across a side wall of the core inlet portion. The indent, groove or recess may provide a local area contraction in the cooling passage of the cast component, which may act to provide enhanced impingement cooling.

The core passage 401 is symmetrical about a line of symmetry which runs transverse to the core inlet portion 408 midway between the first core bridge 421a and the second core bridge 421b. The line of symmetry passes through the first point 405.

Located on the line of symmetry, a distance towards the upstream end 402 from the core inlet portion 408, the core 400 comprises a cylindrical pillar 416. The cylindrical pillar 416 extends away from the core passage 401 such that it can each pass through the sacrificial layer, e.g. wax, once applied, and connect with the ceramic shell. In so doing, the cylindrical pillar 416 extends away from the core passage 401, through the component wall once cast, so as to leave a hole in an exterior facing surface. The hole may allow inspection, e.g. visual inspection, of the cast component. The hole may facilitate core removal, e.g. by leaching. The cylindrical pillar 416 may have any transverse cross-section.

Either side of the line of symmetry, the core passage 401 comprises a pair of c-shaped apertures 418a, 418b. The c-shaped apertures 418a, 418b provide guide vanes in the cooling passage(s) of the cast component. The core passage 401 is shaped to provide a Jennings bend 417a, 417b disposed inwards of each of the guide vanes provided by the c-shaped apertures 418a, 418b

The core passage 401 includes a plurality of apertures 419 therethrough to provide pedestals to aid heat transfer in the cooling passage(s) of the component. For clarity, only one of the apertures 419 is labelled in Figure 4 and Figure 5. Pedestals are merely an example of a suitable feature for aiding heat transfer in the cooling passage(s) of the component that the core 400, e.g. the core passage 401, may be adapted to provide.

The core 400 further comprises a core notch 424. The core notch 424 is provided in the upstream end 402 of the core passage 401. The core notch 424 is disposed on the line symmetry, upstream of the cylindrical pillar 416.

The downstream end 403 has three discrete portions 407a, 407b, 407c, which each correspond to outlets from the cooling passage(s) of the cast component.

The core passage 401 may include one or more core ties to provide additional support or a particular interconnecting flow between the core passages, if required. The need for core ties may have been reduced, if not eliminated, by the core bridge(s).

In a cast component manufactured using the core 400, a pressurised cooling fluid, e.g. air, is supplied to an inlet corresponding to the upper surface 409 of the core inlet portion 408. The pressurised cooling fluid then enters the cooling passages corresponding to the core passage 401. The pressurised cooling fluid flows in all directions away from the region at which a chimney formed by the core inlet portion 408 meets the cooling passages formed by the core passage 401. Accordingly, some of the pressurised cooling fluid exits the cooling passages via each of the outlets formed by the three discrete portions 407a, 407b, 407c of the downstream end 403 of the core passage 401.

Figure 7 shows the exterior of a cast component 700. The cast component 700 was made using the core 400 of Figures 4, 5 and 6. The cast component 700 may be a seal segment for bounding a portion of a main gas path of a gas turbine engine. The component may be a combustion tile. The cast component may comprise, or consist essentially of, an alloy such as a nickel alloy or an aluminium alloy. The alloy may be present as a single crystal.

The cast component 700 comprises an alloy body 701. The body 701 has an upstream end 707 and a downstream end 706. The body 701 comprises an inlet 702 formed by the core inlet portion 408. The inlet 702 has the form of an elongate slot. A pair of apertures 703, 704 are disposed at either end of the inlet 702. The apertures 703, 704 correspond to the second pillars 412a, 412b of the first and second core bridges 421a, 421b respectively.

Towards the upstream end 707 of the body 701, in line with a midpoint of the inlet 702, there is an inspection hole 705. The inspection hole 705 was provided by the cylindrical pillar 416.

The apertures 703, 704 and the inspection hole 705 may each be sealed over with a cap. The caps may be joined to the body 701 using any suitable joining technique, for instance welding.

The body 701 comprises three outlets (not shown) in the downstream end 706. The three outlets were provided by the three discrete portions 407a, 407b, 407c of the downstream end 403 of the core passage 401. Alternatively or additionally, the outlets may be machined into the body 701 to provide outlets that communicate with the internal passages formed by the three discrete portions 407a, 407b, 407c of the downstream end 403 of the core passage 401.

It will be understood that the invention is not limited to the embodiments abovedescribed and various modifications and improvements can be made without departing from the concepts herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.

Claims

1. A core (300) for an investment casting process in which a component to be cast has an internal passageway, the internal passageway being provided by the core (300) , the core (300) comprising: a chimney portion (301); and a core passage (302), the chimney portion (301) extending away from the core passage (302); wherein the chimney portion (301) comprises at least one indent, groove or recess (306).

2. A core (300) according to claim 1, wherein: the chimney portion (301) is perpendicular to the core passage (302); or the chimney portion (301) extends away from the core passage (302) in a non-perpendicular direction, e.g. at an angle of up to 30°, up to 20°, up to 10° or up to 5° from the perpendicular direction; and/or the chimney portion (301) extends away from the core passage (302) at an angle of at least 1° or at least 3° from the perpendicular.

3. A core (300) according to claim 1 or claim 2, wherein the core passage (302) extends from a first end (303) to a second end (304) and the chimney portion (301) connects with the core passage (302) at an intermediate location between the first end (303) and the second end (304).

4. A core (300) according to claim 3, wherein a base (307) of the core passage (302) extends from the first end (303) to the second end (304).

5. A core (300) according to any one of the preceding claims, wherein the chimney portion (301) and the core passage (302) each form an internal passageway in the cast component and the formed internal passageways communicate with each other to provide a continuous internal passageway.

6. A core (300) according to any one of the preceding claims, wherein the indent, groove or recess (306) extends in a transverse direction across the chimney portion (301) .

7. A core (300) according to any one of the preceding claims, wherein the indent, groove or recess (306) is disposed relatively close to the core passage (302).

8. A ceramic shell for an investment casting process in which a component to be cast has at least one internal passageway, the internal passageway(s) being provided by a core (300), the ceramic shell comprising: a core (300) according to any one of claims 1 to 7, the core (300) having an outer layer of a sacrificial material within the ceramic shell, wherein the chimney portion (301) extends between the core passage (302) and the ceramic shell through the sacrificial material.

9. A ceramic shell according to claim 8, wherein the sacrificial material is wax-based.

10. A cast component (700) comprising: at least one internal passageway formed by a core according to claim 8 or claim 9, wherein the internal passageway has a local area contraction corresponding to the indent, groove or recess (306).

11. A cast component (700) according to claim 10, wherein the cast component (700) comprises one or more further caps sealing apertures at one or more further points.

12. A cast component (700) according to claim 10 or claim 11, wherein the cast component (700) is a seal segment for bounding a portion of a main gas path of a gas turbine engine (10) or the cast component is a combustion tile.

13. A gas turbine engine (10) comprising a cast component (700) according to claim 11 or claim 12.

Intellectual Property Office

Application No: GB1803325.8

Claims searched: 1-9

Examiner: Matthew Lawson

Date of search: 1 August 2018

Patents Act 1977: Search Report under Section 17

Documents considered to be relevant:

Category Relevant to claims Identity of document and passage or figure of particular relevance X 1-5,7-9 US 3192578 A (McC0RMICK) - column 3 lines 33-41 & 50-58 and figures 1-5. X 1,2,5-7 CN 20527051 U (SHENYANG) - WPI Abstract Accession No. 16-34728T, paragraph [0019] and figures 1, 5 & 6. X 1,2,5-7 US 2011/0204205 Al (KAMEL) - paragraphs [0043] and figure 6. X 1,2,5-7 US 2016/0319674 Al (GLEINER) - paragraphs [0038] & [0040] and figure 4A. X 1,2,5-7 US 2006/0292005 Al (PIETRASZKIEWICZ) - figure 3. X 1,2,5-7 US 2006/0219379 Al (PRIGENT) - paragraphs [0017] & [0034] and figure 3.