CURING MOLD FOR MANUFACTURING A TURBOMACHINE COMPONENT MADE OF COMPOSITE MATERIAL FROM A PREFORM AND METHOD FOR PRODUCING A COMPONENT BY MEANS OF SUCH A MOLD

Abstract

A curing mold for manufacturing a turbomachine component is made of composite material from a preform, including: a first and a second body defining an air gap receiving the preform; at least one primary channel arranged in the first and/or the second body; an injection member of a pressurized fluid in the primary channels; at least one secondary channel, in which a piston slides, which delimits, on the one hand, a first chamber in communication with the or a primary channel and, on the other hand, a second chamber in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.

Claims

1. Curing mold for manufacturing a turbomachine component from a composite material, starting from a preform made by laying up prepregs comprising reinforcing fibers impregnated in a thermosetting resin, the curing mold comprising: a first body and a second body designed to be fitted together, the first and second bodies each comprising an internal surface, the internal surface comprising a peripheral area at which the first and second bodies are in contact with each other and a central area defining a fixed air gap between the first and second bodies, the shape of the air gap being complementary to the turbomachine component to be manufactured and intended to accommodate the preform; a heating member designed to heat the preform in the air gap to a first temperature, so as to reduce the viscosity of the resin; at least one primary channel formed in the first and/or second body; an injection member designed to inject fluid under pressure into the primary channel(s); at least one secondary channel formed in the first and/or second body, the or each secondary channel receiving a piston installed free to slide inside said secondary channel along a sliding axis and delimiting, on the one hand, a first chamber in communication with the or a primary channel(s), and on the other hand, a second chamber in communication with the air gap, the piston of the or each secondary channel being also designed to compress resin that entered the second chamber of said secondary channel from the preform into the air gap, so as to put the preform under hydrostatic pressure when the preform is located in the air gap, when the heating member heats the preform to the first temperature and when the injection member injects fluid under pressure into the primary channel(s) to the first chamber of said secondary channel.

2. Curing mold according to claim 1, wherein: the heating member is also designed to heat the preform to a second temperature, higher than the first temperature, so as to cure the preform, when said preform is located in the air gap; the piston 24 of the or each of the secondary channels 23 is designed to maintain the compression applied on the resin in the second chamber of said secondary channel, when the preform is located in the air gap, when the heating member heats the preform to the second temperature and when the injection member injects fluid under pressure into the primary channel(s) as far as the first chamber of said secondary channel.

3. Curing mold according to claim 1, wherein the second chamber of the or each secondary channel communicates with the air gap through a nozzle with a cross-section perpendicular to the sliding axis of the piston of said secondary channel, smaller than that of said second chamber.

4. Curing mold according to claim 1, wherein: the reinforcing fibers of the preform are oriented perpendicular to a stacking direction (DE); the sliding axis of the piston of the or each secondary channel is coincident with the stacking direction DE of a portion of the preform facing said secondary channel.

5. Method for manufacturing a turbomachine component made of composite material, making use of the curing mold according to claim 1, starting from a preform made by laying up prepregs comprising reinforcing fibers impregnated in a thermosetting resin, the manufacturing method comprising the following steps: place the preform in the air gap, between the first and second bodies of the curing mold; heat the preform to the first temperature, with resin from the preform entering the second chamber of the secondary channel(s); inject fluid under pressure into the or each primary channel as far as the first chamber of the or each secondary channel, so that the piston of the or each secondary channel compresses the resin that entered the second chamber of said secondary channel from the preform into the air gap, the preform being kept at the first temperature.

6. Manufacturing method according to claim 5, also comprising a subsequent step to heat the preform to a second temperature, higher than the first temperature, so as to cure the preform, the compression applied by the or each piston in the secondary channel(s) on the resin in the second chamber of said secondary channel being maintained, the resin cured in the or each second chamber forming sprue.

7. Manufacturing method according to claim 6, also comprising a subsequent step to demould the preform thus cured, the sprue of cured resin in the second chamber of the secondary channel(s) being broken, so as to obtain the turbomachine component.

8. Manufacturing method according to claim 5, wherein the preform is put under a hydrostatic pressure between 3 and 10 bar inclusive, during the step to inject pressurized fluid into the or each primary channel.

9. Manufacturing method according to claim 5, wherein the preform is put under a hydrostatic pressure between 3 and 7 bar inclusive, during the step to inject pressurized fluid into the or each primary channel.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Other aspects, purposes, advantages and characteristics of the invention will become clear after reading the following detailed description of preferred embodiments of the invention, given as non-limitative examples, with reference to the appended drawings among which:

[0037] FIG. 1 is a diagrammatic sectional view of a curing mold to manufacture a turbomachine component made of a composite material, from a preform, according to one embodiment of the invention, the curing mold being represented without the preform;

[0038] FIG. 2 is a sectional view of the curing mold illustrated in FIG. 1, the preform being located inside the curing mold;

[0039] FIG. 3 is a flow chart of a method of manufacturing a turbomachine component made of composite material using the curing mold illustrated in FIGS. 1 and 2;

[0040] FIG. 4 is a perspective view of an example of a turbomachine component obtained using the manufacturing method illustrated in FIG. 3;

[0041] FIG. 5 is a perspective view of another example of a turbomachine component obtained using the manufacturing method illustrated in FIG. 3;

[0042] FIG. 6 is a longitudinal, diagrammatic sectional view of a turbomachine for an aircraft comprising the turbomachine component illustrated in FIG. 4.

DETAILED DESCRIPTION

[0043] FIGS. 1 and 2 show a curing mold 10 to manufacture a turbomachine component made of a composite material, from a preform 200, according to one embodiment of the invention.

[0044] The preform 200 is made by laying up prepregs comprising reinforcing fibers impregnated in a thermosetting resin. The preform 200 comprises a surplus of resin relative to the quantity of thermosetting resin in the turbomachine component to be manufactured.

[0045] For example, the preform 200 is made by laying up prepregs comprising single-directional carbon fibers impregnated with an epoxy thermosetting resin. These prepregs may for example comprise 34% by mass of epoxy thermosetting resin. In the remainder of the description, the values provided are adapted in particular to a preform 200 made by laying up such prepregs.

[0046] For example, the preform 200 is produced by automated placement of fibers, also known as “AFP”, which stands for “Automated Fiber Placement”. As a variant, the preform 200 can be made by manual or automated laying up by placement of tape, also known as “ATL”, which stands for “Automated Tape Laying”. These laying up techniques are well known to a person skilled in the art.

[0047] Reinforcing fibers for the preform 200 are oriented perpendicular to a stacking direction DE that defines a thickness of the preform 200. The reinforcing fibers are thus stacked along the stacking direction DE. It will be understood that, depending on the geometry of the preform 200, particularly its curvature(s), the stacking direction DE of the reinforcing fibers of the preform 200 may have an orientation that varies from one area of the preform 200 to another.

[0048] For example, in the example shown in FIGS. 1 and 2, the preform 200 is in the form of a rectangular plate. As a variant (not shown), the preform 200 is in the form of a shell.

[0049] The curing mold 10 comprises a first body 11 and a second body 12 designed to be fitted together. Each of the first and second bodies 11, 12 has an internal surface 13, 14 itself comprising a peripheral area 15, 16 in which the first and second bodies 11, 12 are in contact with each other in a clamping direction DS, for example vertical, and a central area 17, 18. The central areas 17, 18 of the internal surface 13, 14 of the first and second bodies 11, 12 define or jointly delimit a fixed air gap 19 that has a shape complementary to the turbomachine part to be manufactured and that will accommodate the preform 200 (FIG. 1).

[0050] The curing mold 10 also comprises a heating member 20 designed to heat the preform 200 in the air gap 19 to a first temperature, so as to reduce the viscosity of the resin (FIG. 2). For example, this makes it possible for the resin of the preform 200 to be distributed uniformly in the air gap 19 of the curing mold 10.

[0051] For example, the first temperature is between 80 and 110° C. inclusive. For example, the first temperature is held for a duration between 30 and 60 minutes inclusive. This time corresponds particularly to a temperature homogenization plateau of the curing mold 10.

[0052] The curing mold 10 also includes at least one primary channel 21 formed in the first and/or second body 11, 12, an injection member 22 designed to inject fluid under pressure into the or each primary channel 21, and at least one secondary channel 23 formed in the first and/or second body 11, 12.

[0053] The or each secondary channel 23 accommodates a piston 24 installed free to slide inside said secondary channel 23 along a sliding axis 25 and delimiting, on one hand, a first chamber 26 in communication with the or with one of the primary channels 21, and on the other hand, a second chamber 27 in communication with the air gap 19.

[0054] The piston 24 of the or each secondary channel 23 is also designed to compress the resin that enters the second chamber 27 of said secondary channel 23 from the preform 200 into the air gap 19, so as to apply hydrostatic pressure to the preform 200 when the preform 200 is located in the air gap 19, when the heating member 20 heats the preform 200 to the first temperature and when the injection member 22 injects fluid under pressure into the primary channel(s) 21 as far as the first chamber 26 of said secondary channel 23. For example, a hydrostatic pressure of between 3 and 10 bar inclusive, preferably between 3 and 7 bar inclusive, is applied to the preform 200.

[0055] “Fluid under pressure” means that the fluid injected into the first chamber 26 of the secondary channel(s) 23, via the primary channel(s) 21, is at such a pressure that the piston 24 of said secondary channel 23 compresses the resin of the second chamber 27 of said secondary channel 23.

[0056] Thus, the curing mold 10 uses surplus resin in the preform 200 in excess of the amount of resin in the turbomachine component to be manufactured to apply hydrostatic pressure to the preform 200. Since this surplus resin is intended to be used in any case during manufacture of the preform 200, there is no loss of resin beyond what is already contained in the preform 200. The curing mold 10 thus avoids a significant additional cost that would be related to an additional supply of resin to apply hydrostatic pressure to the preform 200.

[0057] For example, the heating member 20 is also designed to heat the preform 200 to a second temperature, higher than the first temperature, so as to cure the preform 200, when said preform 200 is located in the air gap 19. Curing the preform 200 polymerizes the resin in the preform 200 and therefore consolidates it so as to obtain the turbomachine component. The second temperature corresponds in particular to a polymerization temperature of the resin of the preform 200. For example, the second temperature is between 170 and 190° C. inclusive, and particularly equal to 180° C. For example, the second temperature is held for a period equal to 2 h.

[0058] The piston 24 of each of the secondary channels 23 can then be designed to maintain the compression applied on the resin in the second chamber 27 of said secondary channel 23, when the preform 200 is located in the air gap 19, when the heating member 22 heats the preform 200 to the second temperature and when the injection member 22 injects fluid under pressure into the primary channel(s) 21 as far as the first chamber 26 of said secondary channel 23. The preform 200 is thus cured under controlled temperature and pressure conditions, so that a turbomachine component with high mechanical performances can be obtained. The compression applied on the resin in the second chamber 27 of the secondary channel 23 by the or each piston 24 is, for example, held during curing. As a variant, it is modified for and/or during curing.

[0059] For example, the heating member 20 is designed to heat the preform 200 through the first and second bodies 11, 12 of the curing mold 10, when the preform 200 fits into the air gap 19 (FIG. 2). For example, the heating member 22 comprises a press like that described below, a heating system using a heat transporting fluid such as oil, or one or more heating cartridges integrated into the first and second bodies 11, 12.

[0060] The fluid injected into the or each primary channel 21 comprises, for example, air, oil, etc.

[0061] The injection member 22 comprises, for example, a compressor 28 designed to apply pressure to the fluid to be injected into the primary channel(s) 21 and an injection conduit 29 in communication, on one hand, with the compressor 28 and, on the other hand, with the primary channel(s) 21.

[0062] The second chamber 27 of the or each secondary channel 23 communicates for example with the air gap 19 through a nozzle 30 with a cross-section perpendicular to the sliding axis 25, smaller than that of said second chamber 27. In this way, after the preform 200 has been cured, the resin cured in the second chamber 27 of the or each secondary channel 23 forms a sprue that breaks easily when demoulding.

[0063] The sliding axis 25 of the piston 24 of the or each secondary channel 23 is, for example, coincident with the stacking direction DE of a portion of the preform 200 facing said secondary channel 23.

[0064] The curing mold 10 may also comprise a press 31 designed to compress the first and second bodies 11, 12 against each other along the clamping direction DS, when the first and second bodies 11, 12 are fitted together (FIG. 2). The press 31 thus clamps the first and second bodies 11, 12 of the curing mold 10 against each other, and resists expansion of the preform 200. The press 30 also assures contact between the peripheral areas 15, 16 of the internal surfaces 13, 14 of the first and second bodies 11, 12 of the curing mold 10 and thus prevents resin leaks.

[0065] FIG. 3 illustrates a method 300 of manufacturing a turbomachine component made of a composite material using the curing mold 10. The manufacturing method 300 includes the following steps: [0066] place 301 the preform 200 in the air gap 19, between the first and second bodies 11, 12 of the curing mold 10; [0067] if applicable, clamp 302 the first and second bodies 11, 12 of the curing mold 10 together along the clamping direction DS; [0068] heat 303 the preform 200 to the first temperature, with resin from the preform 200 entering the second chamber 27 of the secondary channel(s) 23; [0069] inject 304 fluid under pressure into the or each primary channel 21 as far as the first chamber 26 of the or each secondary channel 23, so that the piston 24 of the or each secondary channel 23 compresses the resin that entered the second chamber 27 of said secondary channel 23 from the preform 200 into the air gap 19, the preform 200 being kept at the first temperature. Hydrostatic pressure is thus applied to the preform 200. This hydrostatic pressure may for example be between 3 and 10 bar inclusive, preferably between 3 and 7 bar inclusive.

[0070] The manufacturing method 300 may also include the following steps: [0071] heat 305 the preform 200 to the second temperature, so as to cure the preform 200, the compression applied by the or each piston 24 in the secondary channel(s) 23 on the resin that entered the second chamber 27 of said secondary channel 23 being maintained, the resin cured in the or each second chamber 27 of said secondary channel 23 forming sprue; [0072] if applicable, release 306 the compression applied by the or each piston 24 in the or each secondary channel 23 on the resin that entered into the second chamber 27 of said secondary channel 23; [0073] unmould 307 the preform 200 thus cured, the sprue of cured resin in the second chamber 27 of the secondary channel(s) 23 being broken, so as to obtain the turbomachine component.

[0074] For example, the step to release 306 occurs as soon as the resin in the preform 200 solidifies in the curing mold 10.

[0075] For example, a finishing step is included to remove resin sprue remaining on the cured preform 200, particularly to smooth areas in which the resin sprue broke during demoulding 307.

[0076] FIGS. 4 and 5 each show an example of a turbomachine component 101 made of composite material obtained by use of manufacturing method 300. FIG. 6 shows a turbomachine 100 for an aircraft comprising the turbomachine component 101.

[0077] The turbomachine 100 is a twin spool turbomachine. It comprises a fan 102 for suction of an air stream that is divided downstream from the fan 102 into a core flow circulating in a core flow channel called the core flow stream 103, inside a core of the turbomachine 100, and a bypass flow going around this core in a bypass flow channel, called the bypass flow stream 104.

[0078] The core of the turbomachine 100 comprises, in order along the air flow direction from upstream to downstream, a low pressure compressor 105 also called a booster, a high pressure compressor 106, a combustion chamber 107, a high pressure turbine 108 and a low pressure turbine 109.

[0079] The rotors of the high-pressure compressor 106 and the high-pressure turbine 108 are connected by a shaft called the “high-pressure shaft”, while the rotors of the low pressure compressor 105 and the low pressure turbine 109 are connected by a shaft called the “low pressure shaft” surrounded by the high pressure shaft.

[0080] The turbomachine 100 is clad by a nacelle 110 surrounding the bypass flow stream 104.

[0081] In addition, the rotors of the turbomachine 100 are mounted rotating around a longitudinal direction 111 of the turbomachine 100.

[0082] The low-pressure compressor 105 comprises one or more stators in addition to one or more rotors, arranged alternately with the rotors along the longitudinal direction 111.

[0083] The stators include blades extending radially from a longitudinal direction 111 between an inner shell and an outer shell (not shown) on which said blades are carried by an outer casing 112.

[0084] For example, the turbomachine component 101 forms the outer casing 112 of the low-pressure compressor 105 (FIG. 4). The turbomachine component 101 can also form a sector of the outer casing 112 of the low-pressure compressor 105 (FIG. 5). “Sector” means an angular sector of the outer casing around the longitudinal direction 111. Alternatively (not shown), the turbomachine component 101 forms a rotor drum.