Patent Publication Number: US-2022228540-A1

Title: Aircraft turbojet engine comprising two thrust reverser modules

Description:
CROSS-REFERENCES TO RELATED APPLICATIONS 
     This application claims the benefit of the French patent application No. 2100470 filed on Jan. 19, 2021, the entire disclosures of which are incorporated herein by way of reference. 
     FIELD OF THE INVENTION 
     The present invention relates to an aircraft turbojet engine comprising two thrust reverser modules and a system for securing between two casings of each module, and to an aircraft comprising such a turbojet engine. 
     BACKGROUND OF THE INVENTION 
       FIG. 1  shows an aircraft  100  which conventionally comprises a turbojet engine  150  for generating a thrust to move the aircraft  100  forward. When the aircraft  100  has to brake, it is known practice to use thrust reverser modules  152  which form part of the turbojet engine  150  and which generate a thrust in the opposite direction to the direction of forward travel of the aircraft  100  so as to slow the aircraft down. There is a thrust reverser module  152  to port and to starboard. 
       FIG. 2  is a schematic end-on view of the thrust reverser modules  152 . 
     The turbojet engine  150  and the reverser modules  152  comprise a secondary duct  208  in which a secondary air stream flows from the front to the rear of the aircraft  100 . 
     Each reverser module  152  comprises reverser doors which are movably mounted on the structure of the reverser module  152  and which take up either a retracted position or a deployed position. In the retracted position, the reverser doors do not lie across the secondary duct  208  and do not obstruct the flow of the secondary stream. In the deployed position, the reverser doors lie across the secondary duct  208  and obstruct the flow of the secondary stream. The secondary stream is then directed outwards, towards the front of the turbojet engine  150 , so as to generate a thrust that slows down the aircraft  100 . 
     Each reverser module  152  comprises an inner casing  202  and an outer casing  204 . The casings  202  and  204  each generally have the form of a half-cylinder centered on a longitudinal direction X of the reverser module  152  corresponding to a longitudinal direction of the turbojet engine  150 . 
     For maintenance reasons, the two reverser modules  152  are pivotably mounted on a structure of the turbojet engine  150  and each reverser module  152  is rotatably movable about a horizontal axis  52  positioned at the top of the turbojet engine  150 . 
     The inner casings  202  delimit an internal volume  206  which houses the core of the turbojet engine  150 . The secondary duct  208  is delimited between each inner casing  202  and the corresponding outer casing  204 . 
     So as to secure the two casings  202  and  204  to one another concentrically, it is known practice to fit securing systems  210  which extend radially relative to the longitudinal direction X. In particular, it is known practice to use a securing system  210  which is positioned at 6 o&#39;clock in an area referred to as the “lower fork” and which generally has the shape of a beam extending in a vertical plane XZ. 
       FIG. 3  shows a prior art securing system  210  in section along the line III-III of  FIG. 2  and in the secondary duct  208 . 
     During maintenance of the turbojet engine  150 , the two reverser modules  152  are moved apart by a technician and the securing system  210  is opened to check the components that are housed in the securing system  210 . To this end, the securing system  210  comprises a port-side hood  302  secured between the inner casing  202  and the outer casing  204  of the reverser module  152  to port, and a starboard-side hood  304  secured between the inner casing  202  and the outer casing  204  of the reverser module  152  to starboard. 
     In the operating position ( FIG. 3 ), the starboard-side hood  304  and the port-side hood  302  are held against one another. 
     The port-side hood  302  in this case has a leading edge  308  which faces the secondary stream and which is extended on one of its sides by a port-side flank  310  extending towards the rear of the turbojet engine  150 . The leading edge  308  extends in this case generally parallel to the vertical direction Z. 
     The starboard-side hood  304  in this case comprises only a starboard-side flank  312 . 
     When the port-side hood  302  and the starboard-side hood  304  are in the operating position, the starboard-side flank  312  extends the leading edge  308  on the other of its sides, and there is a channel  314  between the port-side hood  302  and the starboard-side flank  312 . 
     To join the two hoods  302  and  304 , there is a seal  306 , such as an elastomer seal, secured to one of the hoods, in this case the port-side hood  302 , against which seal the other hood, in this case the starboard-side hood  304 , bears. 
     The seal  306  is in a housing  316  formed inside the securing system  210 , generally between the port-side flank  310  and the starboard-side flank  312 . The housing  316  is in fluid communication with the channel  314 . 
     The seal  306  comprises a foot  307  and a sausage  311  rigidly secured to the foot  307  and the securing system  210  comprises a shoe  309  which is secured to the port-side hood  302  in a vertical plane XZ and in which the foot  307  is held. The foot  307  is thus secured in a vertical plane XZ and the sausage  311  protrudes from the foot  307  in a transverse direction Y which is perpendicular to the vertical plane XZ. 
     The seal  306  creates a fluid tight and fireproof seal between the interior of the securing system  210  and the secondary duct  208 . For enhanced sealing, it is known practice to create labyrinths with the aid of metal strips. 
     The securing system  210  in this case comprises a first strip  318  secured to the interior of the port-side hood  302  and a second strip  320  secured to the interior of the starboard-side hood  304 . The two strips  318  and  320  are curved towards one another downstream of the seal  306  relative to the channel  314 . 
     Owing to manufacturing tolerances and assembly tolerances for assembly of the reverser modules  152  on the structure of the turbojet engine  150 , and as a result of the relative movements in flight between the port-side hood  302  and the starboard-side hood  304 , the forces are applied mainly parallel to the transverse direction Y. The seal therefore moves mainly in the transverse direction Y and it is necessary to provide a robust seal, i.e., one with a large diameter so as to ensure sealing and longevity. 
     With a seal this robust, considerable force is needed to close the hoods and it is thus desirable to find a new arrangement for the securing system. 
     SUMMARY OF THE INVENTION 
     One aim of the present invention is to propose an aircraft turbojet engine comprising two thrust reverser modules and comprising a system for securing between an inner casing and an outer casing of each thrust reverser module, wherein the securing system comprises a port-side hood and a starboard-side hood between which is positioned a seal which undergoes less deformation and wherein less force is required to secure the hoods. 
     To this end, it proposes a turbojet engine of an aircraft having a longitudinal direction and a transverse direction perpendicular to the longitudinal direction and comprising:
         a structure,   two thrust reverser modules pivotably mounted on the structure between a close-together position and a spaced-apart position,       

     wherein each thrust reverser module comprises an outer casing generally in the form of a half-cylinder centered on the longitudinal direction, an inner casing generally in the form of a half-cylinder centered on the longitudinal direction, housed inside the outer casing, and
         a securing system for securing, for each thrust reverser module, the inner casing to the outer casing, and comprising:   a first hood secured between the inner casing and the outer casing of one of the reverser modules, and having a leading edge,   a second hood secured between the inner casing and the outer casing of the other of the reverser modules,       

     wherein a housing is formed between the first hood and the second hood and delimited by a securing wall of the first hood extending perpendicularly to the longitudinal direction at the rear of the leading edge,
         a seal comprising a foot and a sausage rigidly secured to the foot, wherein the foot is secured in the housing to the securing wall and wherein the sausage protrudes from the foot in the longitudinal direction, and   a crushing means rigidly secured to the second hood and arranged to crush the sausage towards the securing wall when the second hood goes from the spaced-apart position to the close-together position.       

     With such an arrangement, the sausage is subjected to forces mainly in the longitudinal direction. As a result, the sausage moves mainly in the longitudinal direction, thus limiting the movements in the transverse direction Y owing to the manufacturing and assembly tolerances and the movements in flight, thereby also limiting shearing at its foot. This has the advantage of making it possible to reduce the diameter of the seal and hence the force to be applied when closing the hoods. 
     According to one particular embodiment, the securing system further comprises a first elastic strip with a first end secured in the housing to the first hood, a second free end protruding towards the second hood, and, between the first end and the second end, a flat area generally parallel to the securing wall, wherein the sausage bears against the flat area, and the crushing means is a pushing means rigidly secured to the second hood and arranged so as to move the flat area towards the securing wall when the second hood goes from the spaced-apart position to the close-together position. 
     According to one particular embodiment, the pushing means is a second strip with a first end secured in the housing to the second hood, a second free end protruding towards the first hood and, between the first end and the second end, a flat area generally parallel to the securing wall, wherein in the spaced-apart position, the first strip is in a rest position, wherein the flat area of the second strip is level with or in front of the flat area of the first strip, wherein in the close-together position, the first strip is in an active position in which it is closer to the securing wall than in the rest position, and the flat area of the second strip is positioned behind and against the flat area of the first strip relative to the sausage. 
     Advantageously, the second end of the first strip is curved towards the securing wall and the second end of the second strip is curved away from the securing wall. 
     According to another particular embodiment, the pushing means is a second strip with a first end secured in the housing to the second hood, a second free end protruding towards the first hood and towards the rear of the reverser module, and, between the first end and the second end, a flat area which has an acute angle relative to the securing wall, wherein in the spaced-apart position, the first strip is in a rest position, wherein in the close-together position, the first strip is in an active position in which it is closer to the securing wall than in the rest position, and wherein the flat area of the second strip is positioned so as to come into contact with the second end of the first strip when going from the spaced-apart position to the close-together position. 
     Advantageously, the second end of the first strip is curved towards the securing wall. 
     According to one particular embodiment, the crushing means is a strip a first end of which is secured in the housing inside the second wall of the second hood and a second end of which is free and protrudes towards the first wall of the first hood, the second end is curved away from the securing wall, and in the spaced-apart position, the second end is positioned facing the sausage. 
     Advantageously, a plane of symmetry of the sausage is offset towards the first hood relative to a plane of symmetry of the foot. 
     The invention also proposes an aircraft comprising a turbojet engine according to one of the above variants. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The abovementioned features of the invention, along with others, will become clearer on reading the following description of an embodiment, the description being provided with reference to the attached drawings, in which: 
         FIG. 1  is a side view of an aircraft, 
         FIG. 2  is a schematic end-on view of the reverser modules of a turbojet engine, 
         FIG. 3  is a view in section along the line III-III of  FIG. 2 , of a prior art securing system, 
         FIG. 4  shows a view similar to the view of  FIG. 3  for a securing system according to a first embodiment of the invention, 
         FIG. 5  shows the securing system of  FIG. 4  in the open position, 
         FIG. 6  shows a view similar to the view of  FIG. 3  for a securing system according to a second embodiment of the invention, 
         FIG. 7  shows the securing system of  FIG. 6  in the open position, 
         FIG. 8  shows a view similar to the view of  FIG. 3  for a securing system according to a third embodiment of the invention, and 
         FIG. 9  shows the securing system of  FIG. 8  in the open position. 
     
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       FIG. 1  and  FIG. 2  are identical in the case of the invention and in the case of the prior art, the only differences between the subject matter of the invention and the prior art lying in the structure of the connection system and these differences are only visible in the views in section shown in  FIGS. 4 and 5  for a first embodiment of the invention,  FIGS. 6 and 7  for a second embodiment of the invention and  FIGS. 8 and 9  for a third embodiment of the invention. Therefore, the elements common to the invention and to the prior art bear the same reference signs. 
     The aircraft  100  comprises a turbojet engine  150  having two thrust reverser modules  152  which are equipped with means, such as reverser doors, for diverting the secondary stream outwards and towards the front of the turbojet engine  150  so as to slow down the aircraft  100 . There is one thrust reverser module  152  to port and one to starboard, pivotably mounted on a structure of the turbojet engine  150  between a close-together position for flight and a spaced-apart position for maintenance. The movement of each thrust reverser module  152  is a rotation about a horizontal axis  52 . 
     In the description below, terms relating to a position refer to an aircraft in the normal flight position, i.e., as shown in  FIG. 1 , and the “front” and “rear” positions are relative to the front and the rear of the turbojet engine and relative to the direction of forward travel of the aircraft  100  when the turbojet engine  150  is in operation. 
     In the description below, and by convention, X means the longitudinal direction of the reverser modules which is coincident with the longitudinal direction X of the turbojet engine and oriented towards the front of the aircraft, Y means the transverse direction which is horizontal when the aircraft is on the ground, and Z means the vertical direction which is vertical when the aircraft is on the ground, these three directions X, Y and Z being at right angles to one another. 
     Each reverser module  152  comprises an inner casing  202  and an outer casing  204 . The two casings  202  and  204  each generally have the shape of a half-cylinder centered on the longitudinal direction X of the reverser module  152 . The inner casing  202  is housed inside the outer casing  204  and each casing  202 ,  204  is secured to a structure of the reverser module  152 . The structure of the reverser module  152  may be a part of either of the casings  202 ,  204 . 
     The inner casings  202  delimit an internal volume  206  in which is housed the core of the turbojet engine  150 . The secondary duct  208  is delimited between each inner casing  202  and the corresponding outer casing  204 . 
     At the lower fork, the reverser module  152  comprises a securing system  400 ,  600 ,  800  which is shown in section in  FIGS. 4 to 9  and which secures, for each reverser module  152 , the two casings  202  and  204  to one another concentrically, i.e., secures the inner casing  202  to the outer casing  204  of the reverser module  152  in question. 
       FIG. 4  shows the securing system  400  in the close-together position of operation and  FIG. 5  shows the securing system  400  in the spaced-apart position open for maintenance. 
       FIG. 6  shows the securing system  600  in the close-together position of operation and  FIG. 7  shows the securing system  600  in the spaced-apart position open for maintenance. 
       FIG. 8  shows the securing system  800  in the close-together position of operation and  FIG. 9  shows the securing system  800  in the spaced-apart position open for maintenance. 
     During maintenance of the turbojet engine  150 , the two reverser modules  152  are moved apart by a technician and the securing system  400 ,  600 ,  800  is opened ( FIG. 5 ,  FIG. 7 ,  FIG. 9 ), to check the components that are housed in the securing system  400 ,  600 ,  800 . To this end, the securing system  400 ,  600 ,  800  comprises a first hood  302 , in this case the port-side hood in the figures, secured between the inner casing  202  and the outer casing  204  of one of the reverser modules  152 , in this case to port, and a second hood  304 , in this case the starboard-side hood, secured between the inner casing  202  and the outer casing  204  of the other reverser module  152 , in this case to starboard. 
     The close-together position corresponds to the position of operation ( FIG. 4 ,  FIG. 6 ,  FIG. 8 ) in which the first hood  302  and the second hood  304  are to closest to one another, and the spaced-apart position corresponds to the position of maintenance ( FIG. 5 ,  FIG. 7 ,  FIG. 9 ) in which the first hood  302  and the second hood  304  are furthest from one another. In the position of operation, the second hood  304  is held in position on the structure by securing means such as screw elements. 
     As in the prior art, the first hood  302  has a leading edge  308  which faces the secondary stream which flows parallel to the longitudinal direction X in the secondary duct  208 . The leading edge  308  is in this case generally parallel to the vertical direction Z. 
     The second hood  304  comprises a second flank  312 , in this case to starboard, which extends to the rear and on one of the sides of the leading edge  308  and the first hood  302  has a first flank  310 , in this case to port, rigidly secured to the leading edge  308  and extending to the rear and on the other of the sides of the leading edge  308 . The first flank  310  extends the leading edge  308 . 
     When the first hood  302  and the second hood  304  are in the position of operation, the second flank  312  extends the leading edge  308  and a channel  314  is present between the first hood  302  and the second flank  312 . 
     In the close-together position, the first hood  302  and the second hood  304  delimit between them a housing  316 . 
     The first hood  302  has, to the rear of the leading edge  308 , a securing wall  402  which extends perpendicularly to the longitudinal direction X, i.e., parallel to the plane YZ, and which partially delimits the housing  316  formed inside the securing system  400 ,  600 ,  800  between the first hood  302  and the second hood  304  and in fluid communication with the channel  314 . 
     The securing system  400 ,  600 ,  800  comprises a seal  406 , such as an elastomer seal, which is secured to the securing wall  402  in the housing  316  between the first flank  310  and the second flank  312 . The seal  406  creates a fluid tight and fireproof seal between the interior of the securing system  400 ,  600 ,  800  and the secondary duct  208 . 
     To this end, the seal  406  comprises a foot  407  and a sausage  411  rigidly secured to the foot  407 . The seal  406  is secured in the housing  316  to the securing wall  402  via the foot  407  and, to this end, the securing system  400 ,  600 ,  800  comprises a shoe  409  which is secured to the securing wall  402  and in which the foot  407  is held. 
     The foot  407  is thus secured in the vertical plane YZ perpendicular to the longitudinal direction X and the sausage  411  protrudes towards the rear in the housing  316  from the foot  407  in the longitudinal direction X. 
     In each of the embodiments, the securing system  400 ,  600 ,  800  comprises a crushing means  450 ,  650 ,  850  rigidly secured to the second hood  304  and arranged so as to crush the sausage  411  towards the securing wall  402  when the second hood  304  goes from the spaced-apart position to the close-together position. 
     In the first and second embodiments presented in  FIGS. 4 to 7 , the securing system  400 ,  600  further comprises a first elastic strip  418 , in particular, a metal leaf spring, a first end  418   a  of which is secured in the housing  316  inside the first wall  310  of the first hood  302  and a second end of which  418   b  is free and protrudes towards the second wall  312  of the second hood  304 . Between the first end  418   a  and the second end  418   b , the first strip  418  has a flat area  418   c  which is generally parallel to the securing wall  402 . 
     Thus, in the longitudinal direction X, the seal  406  is positioned between the securing wall  402  and the flat area  418   c  and the sausage  411  bears against the flat area  418   c  of the first strip  418 . 
     The crushing means  450 ,  650  of the securing system  400 ,  600  comprises a pushing means  420 ,  620  which is rigidly secured to the second hood  304  and which is arranged so as to move the flat area  418   c  towards the securing wall  402  when the second hood  304  goes from the spaced-apart position to the close-together position, i.e. when the second hood  304  moves generally parallel to the transverse direction Y owing to the dimensions of the turbojet engine  150 . The action of the pushing means  420 ,  620  on the first strip  418  tends to elastically deform the first strip  418 , in particular, at the join between the first end  418   a  and the flat area  418   c.    
     Thus, the flat area  418   c  moves mainly parallel to the longitudinal direction X, and the sausage  411  is also compressed in the longitudinal direction X. Even if, during its movement, the second hood  304  has spurious movements parallel to the longitudinal direction X, the movements are added to the movements caused by the pushing means  420 ,  620  which are in the same direction and there is therefore no cutting force perpendicular to the longitudinal direction X in the area where the sausage  411  joins the foot  407  and the seal  406  is thus preserved. 
     Moreover, the seal  406  may be smaller since it is only stressed in the longitudinal direction, independently of the transverse direction Y in which the manufacturing and assembly are tolerances, and the movements in flight, are applied, which facilitates the transition to the close-together position. 
     In the spaced-apart position, the first strip  418  is in a rest position and is subjected to the pressure exerted by the sausage  411   
     In the close-together position, the first strip  418  is in an active position in which it is closer to the securing wall  402  than in the rest position and compresses the sausage  411 . 
     In the embodiment of the invention in  FIG. 4  and in  FIG. 5 , the pushing means  420  takes the form of a second elastic or rigid strip  420 , in particular, a metal strip for example, a first end of which  420   a  is secured in the housing  316  inside the second wall  312  of the second hood  304  and a second end  420   b  of which is free and protrudes towards the first wall  310  of the first hood  302 . Between the first end  420   a  and the second end  420   b , the second strip  420  has a flat area  420   c  which is generally parallel to the securing wall  402 . 
     When the second strip  420  is elastic and in the spaced-apart position, it is in a rest position and the flat area  420   c  of the second strip  420  is positioned level with or in front of the flat area  418   c  of the first strip  418 . In the close-together position, the second strip  420  is in an active position in which it is further away from the securing wall  402  than in the rest position and the flat area  420   c  of the second strip  420  is positioned behind and against the flat area  418   c  of the first strip  418  relative to the sausage  411 . Thus, when the second hood  304  moves towards the first hood  302 , the flat area  420   c  of the second strip  420  moves behind in contact with the flat area  418   c  of the first strip  418  and the second strip  420  retracts into its active position while pushing the first strip  418  towards the front, the latter moving into its active position. 
     When the second strip  420  is rigid, it stays in the same position, wherein in the spaced-apart position, the flat area  420   c  of the second strip  420  is level with or in front of the flat area  418   c  of the first strip  418 , and wherein in the close-together position, the flat area  420   c  of the second strip  420  is positioned behind and against the flat area  418   c  of the first strip  418  relative to the sausage  411  and pushes the first strip  418  towards the front, the latter moving into its active position. 
     To facilitate the passage of the second strip  420  behind the first strip  418  when going from the spaced-apart position to the close-together position, the second end  418   b  of the first strip  418  is curved towards the securing wall  402  and the second end  420   b  of the second strip  420  is curved away from the securing wall  402 . Thus, when moving from the spaced-apart position to the close-together position, the two curved ends  418   b  and  420   b  slide one on top of the other so as to move the strips  418  and  420  from their rest positions into their active positions. 
     In the embodiment of the invention of  FIGS. 6 and 7 , the pushing means  620  also takes the form of a second elastic or rigid strip  620 , in particular a metal strip for example, a first end  620   a  of which is secured in the housing  316  inside the second wall  312  of the second hood  304  and a second end  620   b  of which is free and protrudes towards the first wall  310  of the first hood  302  and towards the rear of the reverser module  152 . Between the first end  620   a  and the second end  620   b , the second strip  420  has a flat area  620   c  which has an acute angle relative to the securing wall  402 . According to one particular embodiment, the angle is for example greater than 0° and less than 70°. 
     When the second strip  620  is elastic and in the spaced-apart position, it is in a rest position and in the close-together position, the second strip  620  is in an active position with an angle relative to the securing wall  402  which is smaller than in the rest position. The flat area  620   c  of the second strip  620  is positioned so as to come into contact with the second end  418   b  of the first strip  418  when going from the spaced-apart position to the close-together position. Thus, when the second hood  304  moves closer to the first hood  302 , the flat area  620   c  of the second strip  620  comes into contact with the second end  418   b  of the first strip  418  and owing to the acute angle, the flat area  620   c  pushes the first strip  418  towards the front, the latter moving into its active position. 
     When the second strip  420  is rigid, it stays in the same position, and the flat area  620   c  of the second strip  620  is positioned so as to come into contact with the second end  418   b  of the first strip  418  when going from the spaced-apart position to the close-together position. 
     To facilitate the sliding of the second end  418   b  of the first strip  418  on the flat area  620   c  of the second strip  620 , the second end  418   b  of the first strip  418  is curved towards the securing wall  402 . 
     The strips  418 ,  420 ,  620  also make it possible to create labyrinths which reinforce the sealing action of the seal  406 . 
     In the third embodiment of the invention presented in  FIGS. 8 and 9 , the crushing means  850  of the securing system  800  takes the form of an elastic or rigid strip  820 , in particular a metal strip for example, a first end  820   a  of which is secured in the housing  316  inside the second wall  312  of the second hood  304  and a second end  820   b  of which is free and protrudes towards the first wall  310  of the first hood  302 . 
     In the embodiment of the invention presented in this case, between the first end  820   a  and the second end  820   b , the strip  820  has a flat area  820   c  which is generally parallel to the securing wall  402  and the second end  820   b  is curved away from the securing wall  402 . 
     In the spaced-apart position, the second end  820   b  is positioned facing the sausage  411  parallel to the transverse direction Y, and preferably between the middle and the rear of the sausage  411 . 
     In the close-together position, the second end  820   b  comes into contact with the sausage  411  and it compresses the sausage  411  in a plane dependent on the components X and Y. The behavior and integrity of the sausage  411  are ensured by the fact that it rolls during compression by the second end  820   b . In the close-together position, the strip  820  thus bears against the sausage  411  and creates a fluid tight and fireproof seal. 
     As in the other embodiments, the size of the seal  406  is smaller because the bolt adjustment tolerances do not have to be taken into account entirely since the X component reduces the Y component and less force is required to close the hoods. 
     In the embodiment of the invention presented in  FIGS. 8 and 9 , the plane of symmetry of the sausage  411 , which is parallel to the plane XZ, is offset towards the first hood  302  parallel to the transverse direction Y, relative to the plane of symmetry of the foot  407  parallel to the plane XZ. 
     While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.