GB2550856A - Method of manufacture - Google Patents

Method of manufacture Download PDF

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Publication number
GB2550856A
GB2550856A GB1609171.2A GB201609171A GB2550856A GB 2550856 A GB2550856 A GB 2550856A GB 201609171 A GB201609171 A GB 201609171A GB 2550856 A GB2550856 A GB 2550856A
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GB
United Kingdom
Prior art keywords
component
base plate
recess
manufacturing
additive layer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
GB1609171.2A
Other versions
GB2550856B (en
GB201609171D0 (en
Inventor
M Garry Ian
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB1609171.2A priority Critical patent/GB2550856B/en
Publication of GB201609171D0 publication Critical patent/GB201609171D0/en
Publication of GB2550856A publication Critical patent/GB2550856A/en
Application granted granted Critical
Publication of GB2550856B publication Critical patent/GB2550856B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
    • B22F12/30—Platforms or substrates
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/64—Treatment of workpieces or articles after build-up by thermal means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/60—Treatment of workpieces or articles after build-up
    • B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F3/15—Hot isostatic pressing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/17—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces by forging
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Composite Materials (AREA)
  • Powder Metallurgy (AREA)

Abstract

A method of manufacturing a component comprises providing a base plate (136, figure 2) having a member 32 reversibly connected thereto and forming at least a portion of the component 34 directly on the member using additive layer manufacturing. The additive layer manufacturing method is preferably powder bed additive layer manufacturing. The member may be a tool and the method may include post-processing the component using the tool to locate and hold the component in a rig or machine during post-processing. The member may form a first portion of the component. The first portion is preferably positioned in a recess 38 provided in the base plate and the first portion may be bolted 42 to the base plate. The component may be a flanged component. The component is preferably a metallic component. The method of the invention may form part of a method of manufacturing a gas turbine engine.

Description

METHOD OF MANUFACTURE
TECHNICAL FIELD
The present disclosure concerns a method of manufacture and/or a component produced using said method of manufacture.
BACKGROUND
Additive layer manufacturing can be used to create parts from various materials. One type of additive layer manufacturing suitable for manufacturing metallic parts is powder bed additive layer manufacturing (ALM). In powder bed ALM a laser or electron beam is used to consolidate a powder so as to form a component. The geometry of the component may be specified in an electronic file such as a computer aided design (CAD) drawing. Powder bed methods include direct metal laser sintering (DMLS), electron beam melting (EBM), selective heat sintering (SHS), selective laser melting (SLM), and selective laser sintering (SLS).
Generally, to produce a component using powder bed ALM, a consumable base plate is provided in the ALM machine. The component being manufactured by ALM is built on the base plate layer by layer, which means that once the final component is manufactured it is welded onto the base plate. The base plate is a thick plate and is provided so as to minimise stresses within the manufactured component. Once formed, the component may be stress relieved and then it is removed from the base plate, often using wire electrical discharge machining (EDM). The base plate is then either re-machined to remove distortion or more generally is disposed of and is not reused.
SUMMARY
According to an aspect there is provided a method of manufacturing a component. The method comprises providing a base plate and a member reversibly connected to said base plate. The method further comprises forming at least a portion of the component directly on the member using additive layer manufacturing.
Reversibly connected may also be referred to a removably connected or releasably connected. It will be understood that reversibly connected, removably connected and/or releasably connected mean that the member can be removed from the base plate without causing damage and/or deformation to the base plate and/or to the member.
It will be understood by the person skilled in the art that a base plate is a plate of sufficient thickness to manage residual stresses in the component being manufactured using additive layer manufacturing.
The member may form a first portion of the component.
The base plate may comprise a recess and the member may be provided in said recess.
The member may be mechanically connected to the base plate.
The member may be connected to the base plate using a releasable fastener, for example a bolt, a clamp, an anchor, a pin, and/or a snap fit fastener.
The member may be a tool (e.g. a slave tool). Once the component has been formed using additive layer manufacturing, the method may comprise postprocessing the component. The method may comprise using the tool to locate and hold the component in a rig or machine during post-processing.
Post-processing may include heat treatment and/or machining.
According to an aspect there is provided a method of manufacturing a component. The method comprises providing a first portion of the component and reversibly connecting the first portion to a base plate. The method further comprises forming a second portion of the component directly on the first portion using additive layer manufacturing.
The following are optional features of one or more of the aspects of the present disclosure.
The base plate may comprise a recess, and the method may comprise positioning said first portion in the recess.
The recess may have the same shape as the first portion. The recess may be dimensioned such that the first portion is a close fit with the recess. The recess and the first portion may be dimensioned such that when the first portion is positioned in the recess an exposed surface of the first portion is flush to a surface of the base plate.
The first portion may be connected to the base plate using a releasable fastener, for example a bolt, a clamp, an anchor, a pin, and/or a snap fit fastener.
The first portion may be bolted to the base plate.
The first portion may be bolted to the base plate on an opposite side to that where the second portion is formed.
The method may comprise forming the first portion by casting, forging, hot isostatic pressing, and/or machining.
The component may be a flanged component.
The component may be a combustor casing for a gas turbine engine.
The first portion may define the flange of the component.
The additive layer manufacturing process may be powder bed additive layer manufacture.
The component may be a metallic component.
According to an aspect there is provided a method of manufacturing a gas turbine engine comprising the method according to any one of the previous aspects.
According to an aspect there is provided a method of repairing a component. The method comprises providing a base plate and reversibly connecting the component for repair to the base plate. The method further comprises adding material directly to the component using additive layer manufacturing.
The baseplate may comprise a recess and the method may comprise positioning the component in said recess.
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
DESCRIPTION OF THE DRAWINGS
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 is a schematic of a conventional arrangement for additive layer manufacture; and
Figure 3 is a schematic of an arrangement for additive layer manufacture. DETAILED DESCRIPTION
With reference to Figure 1, a gas turbine engine is generally indicated at 10, having a principal and rotational axis 11. The engine 10 comprises, in axial flow series, an air intake 12, a propulsive fan 13, an intermediate pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, an intermediate pressure turbine 18, a low-pressure turbine 19 and an exhaust nozzle 20. A nacelle 21 generally surrounds the engine 10 and defines both the intake 12 and the exhaust nozzle 20.
The gas turbine engine 10 works in the conventional manner so that air entering the intake 12 is accelerated by the fan 13 to produce two airflows: a first airflow into the intermediate pressure compressor 14 and a second air flow which passes through a bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 14 compresses the airflow directed into it before delivering that air to the high pressure compressor 15 where further compression takes place.
The compressed air exhausted from the high-pressure compressor 15 is directed into the combustion equipment 16 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 17, 18, 19 before being exhausted through the nozzle 20 to provide additional propulsive thrust. The high 17, intermediate 18 and low 19 pressure turbines drive respectively the high pressure compressor 15, intermediate pressure compressor 14 and fan 13, each by suitable interconnecting shaft.
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.
One or more of the components of a gas turbine engine may be manufactured using additive layer manufacturing (ALM). In particular powder bed ALM may be used. Powder bed ALM includes direct metal laser sintering (DMLS), electron beam melting (EBM), selective heat sintering (SHS), selective laser melting (SLM), and selective laser sintering (SLS). Referring to Figure 2, conventionally to manufacture a component for a gas turbine engine using powder bed additive layer manufacturing, a base plate 136 is provided in the ALM machine. The base plate is a thick metallic plate. It is important that the plate is thick so that it does not distort during the ALM process which can be caused due to residual stresses in the component. The component 130 is then formed on the base plate 136, such that the component and the base plate form an integral structure. To form the component, a first portion 132 of the component is formed followed by a second portion 134 of the component, the component being built up in a direction away from the base plate. In ALM the component is formed by depositing layer on layer of material and building up the component in this manner. Often it is necessary to also deposit material to form supports, which can later be removed.
Once the component 130 is formed, the component and the now integral baseplate 136 are removed from the machine. The baseplate is then removed from the component either before or after any required heat treatment requirements, using a method such as wire electrical discharge machining. The base plate is a consumable part and as such it is discarded or recycled once it has been removed from the component.
The present disclosure proposes an alternative method of manufacturing a component using additive layer manufacturing. In the proposed method the baseplate can be reused and the time taken to manufacture a component can be reduced.
Referring to Figure 3, to manufacture the component 30, the first portion 32 of the component is first manufactured. The first portion 32 is manufactured using any suitable method, for example, forging, casting, machining, and/or HIPPING. In the present example, the first portion 32 forms a flange of the component 30. The first portion has a rectangular cross section. The first portion defines an annulus. Threaded recesses 33 are provide in a face (e.g. in the annular face) of the first portion. In the present example four recesses 33 are provided, but in alternative examples any suitable number of recesses may be provided.
The base plate 36 is provided with a recess 38. In the present example, the recess 38 has a rectangular cross section and forms an annulus. However, in alternative embodiments the recess may have any suitable shape. A bolt hole 40 is provided in the base plate and extends from the rear of the base plate (i.e. a surface opposite that where the recess is provided) to the recess. In the present example, the bolt hole 40 is not threaded, but in alternative embodiments the bolt hole may be threaded. In the present example, four bolt holes are provided but in alternative embodiments any suitable number of bolt holes may be provided.
Once the first portion 32 of the component 30 has been manufactured, it is positioned in the recess 38 of the base plate 36. The recess 38 is shaped and dimensioned to receive the first portion 32. In this example, the recess 38 has the same shape as the first portion 32. The recess and first portion are dimensioned such that the first portion does not protrude from the base plate, i.e. when positioned in the recess the exposed surface of the first portion is flush with the surface of the base plate. Once the first portion 32 is positioned in the recess 38, the first portion 32 is bolted to the base plate 36. Bolts 42 are received in the bolt holes 40 and are screwed into the threaded recess 33 of the first portion.
Once the first portion 32 is secured to the base plate 36 using the bolts 42, the second portion 34 of the component is formed. The second portion 34 of the component is formed using powder bed ALM. As such, the second portion 34 is formed by building layers of material from the first portion in a direction away from the first portion. In this way, the first portion and the second portion are integrally formed. The shape of the second portion may be defined by an electronic file such as a computer aided design (CAD) drawing. In the present example, the second portion is conical in shape.
Once the second portion 34 is formed, the component 30 may be further processed, e.g. stress relieved. The component 30 can then be removed from the base plate 36. The component 30 is removed by unbolting the component from the base plate. The base plate 36 can then be reused to form another component.
The component 30 may be further processed, for example the component may be heat treated and/or machined. During the machining process, the threaded recess 33 of the first portion may be removed.
Using the described method to manufacture the component 30 means that lower cost technologies can be used to manufacture the first portion that has simpler geometry than the remainder of the component. In this way, the cost and time to manufacture the component 30 can be reduced.
Further, when using the described method, the base plate 36 can be removed without causing damage to the base plate (or component), and can be reused to form another component. This saves cost in terms of removal of the component from the base plate and also because the base plate is no longer a consumable part.
In the described example, the part bolted to the base plate was a first portion of the component, however, in alternative embodiments, the part may be a tool (e.g. a slave tool). In such examples, the tool may be positioned in the recess of the base plate. The component may then be built directly onto the tool. The tool and the component can then be removed from the base plate. The component can then be further processed (e.g. heat treated and/or machined), and the tool can be used for holding the component in the further processing operations. The slave tools may include single point fast release locators to ease downstream manufacturing processes.
In the described examples, bolts have been used to connect the first portion of the component or the tool to the base plate, but in alternative examples any suitable releasable connector may be used. For example, a clamp, a two part fastener integrally formed with the first portion or tool and the base plate, a snap fit fastener, a pin, and/or an anchor.
In the described example, the material of the first portion is the same material as the second portion, but in alternative embodiments the material of the first portion may be different to the material of the second portion.
The method of manufacture has been described with reference to manufacturing a component for a gas turbine engine, but the method of manufacture can be used for any suitable component in any industry, for example, the marine or nuclear industry.
It will be understood that the described method may in alternative embodiments be used to repair a component. In such embodiments, the component may be connected to the base plate and material may be added to the component using additive layer manufacturing.
It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described 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 subcombinations of one or more features described herein.

Claims (14)

Claims
1. A method of manufacturing a component, the method comprising: providing a base plate and a member reversibly connected to said base plate; and forming at least a portion of the component directly on the member using additive layer manufacturing.
2. The method according to claim 1, wherein the member forms a first portion of the component.
3. A method of manufacturing a component, the method comprising: providing a first portion of the component; reversibly connecting the first portion to a base plate; and forming a second portion of the component directly on the first portion using additive layer manufacturing.
4. The method according to claim 2 or 3, wherein the base plate comprises a recess, and the method comprises positioning said first portion in the recess.
5. The method according to any one of claims 2 to 4, wherein the first portion is bolted to the base plate.
6. The method according to claim 5, wherein the first portion is bolted to the base plate on an opposite side to that where the second portion is formed.
7. The method according to any one of the previous claims comprising forming the first portion by casting, forging, hot isostatic pressing, and/or machining.
8. The method according to any one of the previous claims, wherein the component is a flanged component.
9. The method according to claim 8, wherein the first portion defines the flange of the component.
10. The method according to claim 1, wherein the member is a tool, and once the component has been formed using additive layer manufacturing, the method comprises post-processing the component and wherein the method comprises using the tool to locate and hold the component in a rig or machine during postprocessing.
11. The method according to claim 10, wherein the base plate comprises a recess and the member is provided in said recess.
12. The method according to any one of the previous claims, wherein the additive layer manufacturing process is powder bed additive layer manufacture.
13. The method according to any one of the previous claims, wherein the component is a metallic component.
14. A method of manufacturing a gas turbine engine comprising the method according to any one of the previous claims.
GB1609171.2A 2016-05-25 2016-05-25 Method of manufacture Active GB2550856B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1609171.2A GB2550856B (en) 2016-05-25 2016-05-25 Method of manufacture

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1609171.2A GB2550856B (en) 2016-05-25 2016-05-25 Method of manufacture

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GB201609171D0 GB201609171D0 (en) 2016-07-06
GB2550856A true GB2550856A (en) 2017-12-06
GB2550856B GB2550856B (en) 2019-09-25

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2583578A (en) * 2019-03-26 2020-11-04 Sst Tech Limited Manufacturing method and components manufactured using the method
FR3108870A1 (en) * 2020-04-06 2021-10-08 Safran Helicopter Engines Modular platform for additive manufacturing on a powder bed of a part with an axis of revolution

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6042774A (en) * 1995-03-30 2000-03-28 Eos Gmbh Electro Optical Systems Method for producing a three-dimensional object
US20100034983A1 (en) * 2008-08-08 2010-02-11 Panasonic Electric Works Co., Ltd. Method for producing a three-dimensionally shaped object
WO2015009444A1 (en) * 2013-07-15 2015-01-22 United Technologies Corporation Method of additively manufacturing articles incorporating a substrate

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6042774A (en) * 1995-03-30 2000-03-28 Eos Gmbh Electro Optical Systems Method for producing a three-dimensional object
US20100034983A1 (en) * 2008-08-08 2010-02-11 Panasonic Electric Works Co., Ltd. Method for producing a three-dimensionally shaped object
WO2015009444A1 (en) * 2013-07-15 2015-01-22 United Technologies Corporation Method of additively manufacturing articles incorporating a substrate

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2583578A (en) * 2019-03-26 2020-11-04 Sst Tech Limited Manufacturing method and components manufactured using the method
FR3108870A1 (en) * 2020-04-06 2021-10-08 Safran Helicopter Engines Modular platform for additive manufacturing on a powder bed of a part with an axis of revolution
WO2021205096A1 (en) * 2020-04-06 2021-10-14 Safran Helicopter Engines Modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed

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Publication number Publication date
GB2550856B (en) 2019-09-25
GB201609171D0 (en) 2016-07-06

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