Cold flap of rear nozzle
Patent Information
- Application Number
- FR2023000956
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- Filing Date
- 2023-02-02
- Publication Date
- 2025-02-21
- Estimated Expiration
- 2043-02-02
Smart Images
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Abstract
Description
Title of the invention: Cold flap for a rear-body nozzle Technical field
[0001] The present invention relates to the field of variable-section nozzles for the rear of turbojet engines. It relates more particularly to the adjustable flaps with which such nozzles are equipped. Prior art
[0002] A turbojet generally comprises, from upstream to downstream in the direction of gas flow, a fan, one or more compressor stages, a combustion chamber, one or more turbine stages and an ejection channel, in which a so-called reheat or post-combustion device may or may not be provided. The exhaust duct consists of a casing and a nozzle, in which the combustion gases expand. It is common to use a variable-section nozzle, possibly with an afterburner, in order to regulate the flow of ejected gases according to the turbojet engine speed.
[0003] In this type of turbojet, the variable section nozzle comprises internal flaps or hot flaps channeling the main air flow as well as external flaps or cold flaps guiding the cooling flow. The internal flaps are actuated directly by control levers so as to modify the profile of the primary flow of the turbomachine engine (i.e. the ejection section(s) depending on whether it is a simple convergent or a convergent / divergent nozzle). In order to synchronize the movements of the external flaps with that of the internal flaps, a connecting rod connects each external flap to the control lever of the internal flaps.
[0004] External flaps are generally made up of an internal box for stiffening the flap and integrating the kinematic elements of the flap, such as yokes, and an upper web for closing the box and ensuring the aerodynamic flow. The box and the web are assembled together by metal rivets. Document US 7,533,533 discloses a variable section nozzle equipped with external flaps.
[0005] This type of external flap architecture is not optimized with regard to its overall mass. However, it is important to control the mass of the flaps of the variable section nozzle because it is very far from the center of gravity of the aircraft and therefore impacts its maneuverability. Statement of the invention
[0006] It is therefore desirable to be able to propose a solution making it possible to reduce the mass of the external or cold flaps in a nozzle with variable afterbody section. turbojet engine while meeting performance and nozzle integration requirements.
[0007] To this end, the present invention proposes an external flap or cold flap for a variable-section nozzle of an aeronautical engine afterbody comprising a flap body extending in a longitudinal direction between an upstream edge and a downstream edge delimiting a trailing edge of the afterbody nozzle and in a transverse direction between first and second transverse edges, the flap body comprising a first portion extending in the axial direction between the downstream edge and an intermediate position between the upstream and downstream edges of said flap body, characterized in that the flap body further comprises a second portion extending in the axial direction between the intermediate position and the downstream edge of the flap body,in that the second portion has in cross section a general omega shape defining a stiffener in the central part of the second portion and first and second flattened parts adjacent to the stiffener, and in that a stiffening bar is fixed on said first and second flattened parts on the side of the internal face of the shutter body, said stiffening bar extending in the transverse direction.
[0008] The external flap or cold flap according to the invention comprises a number of constituent parts lower than the number used until now, which makes it possible to significantly reduce the overall mass at the nozzle end. Furthermore, the simplification of the design of the flap of the invention does not result in a reduction in the performance of the flap. Indeed, the flap body provides the aerodynamic function necessary for channeling and guiding the secondary or cooling flow. The omega shape in the second portion corresponding to the free end of the flap forming a trailing edge of the nozzle makes it possible to give the flap longitudinal stiffness. Furthermore, the stiffening bar ensures a rigid junction in the transverse direction between the flattened parts corresponding to the transverse ends of the omega stiffener.This gives the shutter good dynamic resistance by preventing any deformation of the stiffener (elimination of the flapping of the flattened parts) under the effect of aerodynamic loads.
[0009] According to a particular characteristic of the invention, the shutter further comprises two U-shaped upstream yokes fixed to the first portion of the shutter body on the side of the internal face of said shutter body and a U-shaped downstream yoke fixed to the stiffening bar.
[0010] According to another particular characteristic of the invention, the shutter body is made of ceramic matrix composite material. In this case, the stiffening bar is preferably made of ceramic matrix composite material in order to avoid expansions. differentials between the shutter body and the stiffening bar.
[0011] According to another particular characteristic of the invention, the shutter body is made of metallic material.
[0012] The invention also relates to a variable section nozzle for the afterbody of an aeronautical engine comprising a series of internal flaps and a series of external flaps according to the invention, the movement of the external flaps being synchronized with the movement of the internal flaps by connecting rods.
[0013] The invention also relates to an aeronautical engine comprising an afterbody equipped with a variable section nozzle according to the invention and an aircraft comprising at least one such engine. Brief description of the drawings
[0014] [Fig-1] [Fig.l] is a schematic perspective view of the external face of a shutter external in accordance with one embodiment of the invention,
[0015] [Fig.2] [Fig.2] is a schematic perspective view of the internal face of an external shutter in accordance with one embodiment of the invention,
[0016] [Fig.3] [Fig.3] is a cross-sectional view of a first portion of the flap of [Fig.l],
[0017] [Fig.4] [Fig.4] is a cross-sectional view of a second portion of the flap of [Fig.l],
[0018] [Fig.5] [Fig.5] is a radial sectional view of a variable-section nozzle equipped with the external flap of Figures 1 to 4. Description of the embodiments
[0019] Figures 1, 2, 3 and 4 show an external flap or cold flap intended to be mounted in an articulated manner on a variable section nozzle of a turbojet afterbody according to an embodiment of the invention.
[0020] The flap 100 comprises a flap body 110 extending, in a longitudinal direction D1 corresponding to the axial direction of the variable-section nozzle, between an upstream edge 111 and a downstream edge 112 intended to delimit a trailing edge of the afterbody nozzle on which it is mounted. The flap body 110 also extends, in a transverse direction DT corresponding to the circumferential direction of the variable-section nozzle, between first and second transverse edges 113 and 114. The flap body 110 comprises an external face 110a shown in [Fig.l] and an internal face 110b shown in [Fig.2].
[0021] The flap body 110 comprises a first portion 115 which extends in the longitudinal direction DL between the upstream edge 111 and an intermediate position 116 between the upstream 111 and downstream 112 edges of the flap body and in the transverse direction DT between the transverse edges 113 and 114. As illustrated in [Fig.3], the first portion has a cross-sectional arc shape corresponding substantially to the curvature of the external casing of the nozzle at the end of which the flap 100 is intended to be positioned.
[0022] According to the invention, the flap body 110 further comprises a second portion 117 extending in the longitudinal direction DL between the intermediate position 116 and the downstream edge 112 of the flap body and in the transverse direction DT between the transverse edges 113 and 114. As illustrated in FIGS. 1 and 4, the second portion 117 has a general omega shape in cross section. The central portion 1170 of the second portion rises progressively in a radial direction DR from the intermediate position 116 where its height is minimal and up to the downstream edge 112 relative to where its height is maximal. The central portion 1170 thus defines a stiffener 118 in the second portion. The second portion 117 further comprises first and second flattened portions 117a and 117b adjacent to the stiffener 118.
[0023] The omega shape in the second portion corresponds to the free end of the flap 100 intended to form the trailing edge of the nozzle. The presence of the stiffener 118 makes it possible to give the flap a longitudinal rigidity capable of supporting the loads to which the flap is subjected in operation.
[0024] Still in accordance with the invention and as illustrated in Figures 2 and 4, a stiffening bar 130 is fixed to the first and second flattened parts 117a and 117b on the side of the internal face 110b of the flap body 110, the stiffening bar 130 extending in the transverse direction DT. The stiffening bar 130 ensures a rigid junction in the transverse direction between the flattened parts 117a and 117b corresponding to the transverse ends of the omega-shaped stiffener 118. This gives the flap good dynamic strength by preventing any deformation of the stiffener 118 (suppression of the flapping of the flattened parts) under the effect of aerodynamic loads.
[0025] A U-shaped downstream yoke 140 is fixed to the stiffening bar 130. The downstream yoke 140 is intended to be connected to a movement synchronization rod with internal flaps or hot flaps of a variable section nozzle.
[0026] The flap 100 also comprises first and second U-shaped upstream yokes 150 and 160 fixed to the flap body 110 in the vicinity of the upstream edge 111. The upstream yokes 150 and 160 are intended to be connected to a downstream end of an external casing of a variable-section nozzle.
[0027] The shutter body 110 may be made of a metallic material or a ceramic matrix composite (CMC) material. CMC materials withstand temperatures ranging from 600°C to 1400°C. In the case of a metallic material, the stiffening bar 130, the downstream yoke 140 and the upstream yokes 150 and 160 are also made of metallic material. The stiffening bar 130 and the upstream yokes 150 and 160 are fixed to the internal face 110b of the shutter body 110 by rivets or bolted connections (not shown in [Fig.2]). The downstream yoke 140 can be fixed to the stiffening bar 130 by rivets, bolted connections or by brazing.
[0028] In the case of a CMC material, the shutter body 110 comprises a fibrous reinforcement made of carbon or silicon carbide (SiC) fibers and an at least partially ceramic matrix such as a SiC matrix. The manufacture of the shutter body begins with the manufacture of a fiber blank by three-dimensional (3D) weaving carried out in a known manner using a jacquard-type loom on which a bundle of warp threads has been arranged in a plurality of layers, the warp threads being linked by weft threads. For the weaving of the fiber blank, ceramic fiber yarns may be used, for example SiC fiber yarns such as those marketed by the Japanese company Nippon Carbon under the name "Hi-Nicalon S", or carbon fiber yarns. The weave may be of the interlock type. Other three-dimensional weave weaves may be used, such as multi-plain or multi-satin weaves.Reference may be made to document WO 2006 / 136755.
[0029] Once the fibrous blank has been woven, the outline of the blank is cut and shaped so as to obtain a fibrous preform having a shape close to that of the shutter body to be produced.
[0030] The fiber preform is then densified in order to form a shutter body made of CMC material. The densification of the fiber preform intended to form the fiber reinforcement of the shutter body to be manufactured consists of filling the porosity of the preform, in all or part of its volume, with the material constituting the matrix. This densification can be carried out in a manner known per se using the liquid process (CVL) or the gas process (CVI), or the ceramic charge injection process (Slurry Cast) or the silicon alloy impregnation process (MI or RMI) or even using a sequence of one or more of these processes.
[0031] The liquid method involves impregnating the preform with a liquid composition containing a precursor of the matrix material. The preform is placed in a sealable mold with a housing having the shape of the final molded blade. The mold is then closed and the liquid matrix precursor (e.g., a resin) is injected throughout the housing to impregnate the entire fiber portion of the preform.
[0032] The transformation of the precursor into a matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after elimination of any solvent and crosslinking of the polymer, the preform always being maintained in the mold having a shape corresponding to that of the part to be produced.
[0033] In the case of the formation of a ceramic matrix, the heat treatment consists of pyrolyzing the precursor to transform the matrix into a ceramic matrix depending on the precursor used and the pyrolysis conditions. For example, liquid ceramic precursors, in particular SiC or SiCN, may be resins of the polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type. Several consecutive cycles, from impregnation to heat treatment, may be carried out to achieve the desired degree of densification.
[0034] Densification of the preform can also be carried out by polymer impregnation and pyrolysis (PIP), or by impregnation of a slip ("slurry cast"), containing for example SiC and organic binders, followed by infiltration with liquid silicon ("Melt infiltration").
[0035] The densification of the fiber preform can also be carried out, in a known manner, by gaseous means by chemical vapor infiltration of the matrix (CVI). The fiber preform corresponding to the fiber reinforcement of the shutter body to be produced is placed in a furnace into which a reaction gas phase is admitted. The pressure and temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the matrix by deposition, at the heart of the material in contact with the fibers, of a solid material resulting from a decomposition of a constituent of the gas phase or from a reaction between several constituents, unlike the pressure and temperature conditions specific to CVD ("Chemical Vapor Deposition") processes which exclusively lead to a deposition on the surface of the material.
[0036] The formation of a SiC matrix can be achieved with methyltrichlorosilane (MTS) giving SiC by decomposition of the MTS.
[0037] Densification combining liquid and gaseous routes can also be used to facilitate implementation, limit costs and manufacturing cycles while obtaining satisfactory characteristics for the intended use.
[0038] After densification, the shutter body 110 is obtained from CMC material.
[0039] When the shutter body 110 is made of CMC material, the stiffening bar- fication 130 is also made of CMC material. This prevents differential expansion between the shutter body and the bar. If the stiffening bar were made of metallic material, differential expansion would occur during temperature increases between the CMC shutter body and the metal bar due to the difference in expansion coefficient between the two materials, thus causing thermomechanical stresses in the shutter.
[0040] In the case of a shutter body and a CMC stiffening bar, the yokes metal parts are fixed to the shutter body or to the stiffening bar by bolted connections or assemblies, comprising thermal compensation conical bushings or washers, in order to maintain the assembly tension, whatever the operating temperature.
[0041] In the case of a shutter body and a stiffening bar made of metallic material, the connections or assemblies are bolted, without thermal compensation systems since the materials expand in the same way (no difference in expansion coefficient).
[0042] [Fig. 5] illustrates a variable-section nozzle 200 of an aeronautical engine or turbojet engine afterbody equipped with cold flaps or external flaps according to the invention. More precisely, the variable-section nozzle 200 comprises an internal casing 201 channeling a flow Fi corresponding to the primary flow or hot flow coming from the combustion chamber of the engine. The nozzle also comprises an external casing 202 forming with the primary casing a circulation channel of a flow F2 corresponding to the secondary flow or cold flow coming from the engine fan.
[0043] The nozzle 200 further comprises a series of internal movable flaps or hot flaps 210, a series of external movable flaps or cold flaps 100 corresponding to the external flap 100 described previously, a control lever 230 connected, on the one hand, to a jack-type actuator 270 and, on the other hand, to several internal flaps 210. [Fig. 5] being a partial view of the nozzle 100, only an internal flap 210, an external flap 100 and a control lever 230 are shown in [Fig. 5]. The nozzle is of course composed of a ring of internal flaps 210 and a ring of external flaps 100 and a plurality of control levers 230 distributed in an annular manner between the internal flaps 210 and external flaps 100. The control lever 230 is connected to the internal flap 210 by first arms 231 and second arms 232. Under the effect of the actuator 270, the control lever 230 pivots in the double direction P230 indicated in [Fig.5], the internal flap 210 connected to the lever 230 then pivoting in the same direction in order to modify (reduce or enlarge) the ejection section of the nozzle 200. As shown in [Fig.5], the external flap 100 is connected to the control lever 230 by a connecting rod 240. The connecting rod 240 comprises a rod 241 comprising at its two ends respectively a first head 242 and a second head 243. The first head 242 is connected to the control lever 230 by a movable link 250 while the second head 243 is connected to the external movable flap 100 by the downstream yoke 140 of said flap. The connecting rod 240 ensures the synchronization of the movements between the internal flap 210 and the external flap 100 to which it is connected by transmitting to the external flap 100 the pivoting movements of the internal lever 210 controlled by the lever 230.
Claims
Claims
1. External flap or cold flap (100) of a variable-section nozzle (200) of an aeronautical engine afterbody comprising a flap body (110) extending in a longitudinal direction (DL) between an upstream edge (111) and a downstream edge (112) delimiting a trailing edge of the afterbody nozzle and in a transverse direction (DT) between first and second transverse edges (113, 114), the flap body (110) comprising a first portion (115) extending in the longitudinal direction between the upstream edge (111) and an intermediate position (116) between the upstream and downstream edges of said flap body, characterized in that the flap body (110) further comprises a second portion (117) extending in the longitudinal direction (DL) between the intermediate position (116) and the downstream edge (112) of the shutter body,in that the second portion (117) has in cross section a general omega shape defining a stiffener (118) in the central part of the second portion and first and second flattened parts (117a, 117b) adjacent to the stiffener, and in that a stiffening bar (130) is fixed on said first and second flattened parts on the side of the internal face (110b) of the shutter body (110), said stiffening bar extending in the transverse direction (DT).,
2. Shutter according to claim 1, further comprising two U-shaped upstream yokes (150, 160) fixed to the first portion (115) of the shutter body (110) on the side of the internal face (110b) of said shutter body and a U-shaped downstream yoke (140) fixed to the stiffening bar (130).
3. A shutter according to claim 1 or 2, wherein the shutter body (110) is made of ceramic matrix composite material.
4. Shutter according to claim 3, in which the stiffening bar (130) is made of ceramic matrix composite material.
5. A shutter according to claim 1 or 2, wherein the shutter body (110) is made of metallic material.
6. Variable section nozzle (200) for an aeronautical engine afterbody comprising a series of internal flaps (210) and a series of external flaps (110) according to any one of claims 1 to 5, the movement of the external flaps being synchronized with the movement of the
7. internal flaps by connecting rods (240). Aeronautical engine comprising an afterbody equipped with a variable section nozzle (200) according to claim 6.
8. Aircraft comprising at least one engine according to claim 7.