Abstract:
Ventilation of an internal compartment of a fairing device of a propulsion assembly in an aircraft moving at low speed on the ground or when it is stopped cannot be provided optimally using a conventional dynamic air intake. To solve this problem, the use of a fan housed within the internal compartment is proposed, for which the fan propeller can alternately be coupled to an accessory gear box to drive the fan propeller, and uncoupled from the accessory gear box when it is unnecessary to drive the fan propeller or when it represents a danger.

Description:
TECHNICAL FIELD 
       [0001]    This disclosure relates to an aircraft propulsion assembly including at least one fairing device and is particularly applicable to cooling of a defined compartment inside such a fairing device. 
         [0002]    The disclosure is indifferently applicable to propulsion assemblies comprising a turbojet and propulsion assemblies comprising a turboprop or propulsion assemblies comprising an open rotor type turbojet. 
         [0003]    More precisely, the fairing device according to the disclosure may be of the type delimiting the external boundary of a bypass flow channel of a double flow turbojet, or of the type separating the bypass flow channel and the core of a double flow turbojet, or of the type delimiting the external boundary of a turboprop or an open rotor turbojet. 
         [0004]    The disclosure also relates to an aircraft on which such a propulsion assembly is installed, as well as a method of ventilating an internal compartment in a fairing device of such a propulsion assembly. 
       BACKGROUND 
       [0005]    In a propulsion assembly in which the turbine engine is a turbojet, the external fairing device that surrounds the turbojet usually comprises an outer annular wall or envelope and an inner annular wall or envelope. The outer annular wall forms an external fairing along which the relative wind flows during flight, while the inner annular wall will guide an air flow supplying the turbine engine. In the case of a double flow turbojet, the air flow directed by the inner annular wall is the bypass flow propelled by the fan and that flows in the downstream direction around the turbojet core. 
         [0006]      FIG. 1  is a partial axial sectional view of a propulsion assembly  10  of a known type of aircraft, comprising a double flow turbojet  12  and an external fairing device  14  surrounding this turbojet. 
         [0007]    As shown in this figure, the outer annular wall  16  surrounds the propulsion assembly  10  so as to guide relative wind  18  around the propulsion assembly while the inner annular wall  20  directs the air flow  22  penetrating in the propulsion assembly at the upstream end, and the bypass flow stream  24  originating from the above mentioned air flow  22  and flowing around the core  26  of the turbojet  12  at the downstream end. 
         [0008]    Throughout this description, the “upstream” and “downstream” directions are defined relative to the global gas flow direction in the turbine engine and the terms “forward” and “aft” should be considered relative to a direction of motion F of the aircraft under the effect of the thrust applied by the turbojet  12 , this direction being parallel to a longitudinal axis  72  of the turbojet. 
         [0009]    The outer  16  and inner  20  annular walls delimit an internal compartment  28  between them in the external fairing device  14  also called the “fan compartment” because of its position adjacent to the fan  30 , between an air intake  32  and a thrust inverter  34 . 
         [0010]    In general, the outer wall  16 , an upstream portion of the inner wall  20  corresponding to the air intake  32  and a downstream portion of the inner wall  20  corresponding to the thrust inverter  34 , form part of a nacelle of the propulsion assembly  10 . On the other hand, an intermediate portion of the inner wall  20  that delimits the internal compartment  28  forms part of an intermediate casing  35  fixed to the turbojet core  26 . 
         [0011]    The internal compartment  28  usually contains an accessory control box  36  also called the AGB (Accessory Gear Box) that mechanically connects a rotor  38  of the turbine engine to one or several accessories such as a starter. In the example shown, the rotor  38  concerned is a high pressure compressor rotor and is connected to the AGB  36  through an intermediate shaft  40  extending from the turbojet core  26  as far as the internal compartment  28 . 
         [0012]    Furthermore, the internal compartment  28  is usually used to house one or several systems such as an Engine Control Unit (ECU), although none of these systems are shown in the sectional plane in  FIG. 1 . 
         [0013]    Some of these systems usually require cooling in order to operate satisfactorily. 
         [0014]    Furthermore, safety standards impose that the concentration of inflammable vapours in the air inside the internal compartment  28  should not exceed a predefined maximum level, such that the internal compartment must be ventilated. “Ventilation” means that the air must be renewed regularly within the internal compartment  28 . 
         [0015]    The external fairing device  14  usually comprises an air inlet orifice  42  and an air exhaust orifice  43  formed in the outer wall  16 , to ventilate the internal compartment  28  and to cool any systems contained in it. The two orifices  42  and  43  are usually diametrically opposite as shown in  FIG. 1 . Furthermore, the air inlet orifice  42  is usually arranged close to the upstream end of the internal compartment  28  while the exhaust orifice is typically arranged close to the downstream end of the internal compartment  28 . 
         [0016]    At the air inlet orifice  42 , the outer wall  16  is usually profiled so as to form a dynamic air intake. To achieve this, the upstream edge  44  of the air inlet orifice  42  may for example be curved inwards into the internal compartment  28  as shown in  FIG. 1  to form an air intake of the type typically referred to as “NACA”, to facilitate penetration of the air boundary layer circulating along the outer wall  16 , in the air inlet orifice  42 . As a variant or as a complement, the downstream edge of the air inlet orifice  42  may be convex outwards to form a scoop, which also facilitates sampling of air circulating along the outer wall  16 . As a variant, such a scoop may be formed from an add-on part on the outer wall  16 , the add-on part facing the air inlet orifice  42 . 
         [0017]    The air flow that enters the internal compartment  28  then forms a ventilation flow  46  circulating in the internal compartment and that finally goes out through the air exhaust orifice  43 . 
         [0018]    However, the cooling efficiency of the internal compartment  28  then depends on the speed of the relative wind  18  surrounding the external fairing device  14  and therefore the aircraft advance speed. 
         [0019]    Thus, when the aircraft moves at low ground speed or is stopped, the above-mentioned dynamic air intake becomes inoperative and the internal compartment  28  of the external fairing device  14  is only cooled by natural convection through the air inlet orifice  42  and the air exhaust orifice  43 , but this may be insufficient. 
         [0020]    One solution for providing satisfactory ventilation and cooling whenever possible under these low speed conditions consists of oversizing the air inlet  42  and air exhaust  43  orifices, and/or exaggerating the aerodynamic profile of the outer wall  20  at the edge of the air inlet orifice  42 , so as to increase the ventilation flow  46 . 
         [0021]    However, this solution penalises the aerodynamic drag of the propulsion assembly, particularly due to an increase in the ram drag during flight, and particularly during the cruise phase. 
         [0022]    Furthermore, if a fire occurs in the internal compartment  28 , the circulation of relatively large ventilation air flow  46  is not desirable because this increases the oxygen content in the air inside the internal compartment, which may make it more difficult to put the fire out. The external fairing devices are usually equipped with a fire fighting system designed to output an extinguishing agent within the internal compartment  28 . The relatively large ventilation air flow then makes it necessary to oversize the fire fighting system so that it will be capable of maintaining a sufficient concentration of extinguishing agent inside the internal compartment  28  in case of fire. 
         [0023]    In general, in the case of a fire, the ventilation air flow  46  in the internal compartment  28  cannot be interrupted or at least reduced, which tends to reduce the efficiency of the extinguishing agent. 
         [0024]    Furthermore, in double flow turbojets, as shown in  FIG. 1 , the bypass flow  24  is separated from the turbojet core  26  by an internal fairing device  48  comprising an outer wall  50  and an inner wall  52  together delimiting an internal compartment  54 , typically called the “core compartment”. The outer wall  50  is sometimes called the IFS (Inner Fixed Structure). 
         [0025]    In order to limit the concentration of inflammable vapours, this internal compartment  54  also has to be ventilated, which is usually done by an air inlet orifice  56  usually on the upstream side and an air exhaust orifice  58  usually on the downstream side. These orifices  56  and  58  carry the circulation of a ventilation air flow  60  inside the internal compartment  54 . The orifices  56  and  58  are preferably diametrically opposite each other. 
         [0026]    In particular, the air exhaust orifice  58  is preferably arranged downstream from a downstream end  62  of the external fairing device  14  such that the air pressure circulating along the outer wall  50  of the internal fairing device  48  at the air exhaust orifice  58  is as low as possible. As a variant, the air exhaust orifice  58  may communicate with a channel passing through an arm connected to the external fairing device  14  and opening up on the outside of the propulsion assembly through the outer wall  16  of the external fairing device  14 . 
         [0027]    The air inlet orifice  56  may be in the form of a dynamic intake provided that the outer wall  50  is given an appropriate conformation, as explained above concerning the external fairing device  14 . 
         [0028]    Furthermore, circulation of the ventilation flow  60  in the internal compartment  54  also provides a way of cooling any systems housed within this compartment, if necessary. 
         [0029]    However, the ventilation flow  60  passing through the internal compartment  54  of the internal fairing device  48  may be insufficient, particularly in turbojets with high dilution ratios. 
         [0030]    However, the solution consisting of oversizing the air inlet  56  and air exhaust  58  orifices penalises the performances of the turbojet and also has the disadvantages described above concerning the risk of fire. 
         [0031]    Similar problems arise concerning the fairing device surrounding the core of a turboprop or an open rotor turbojet. 
       SUMMARY 
       [0032]    A purpose of the disclosure is particularly to provide a simple, economic and efficient solution to at least part of these problems, at least partly avoiding the above mentioned disadvantages. 
         [0033]    One particular purpose of the disclosure is to provide a solution to these problems that consumes little energy and that has all the guarantees necessary for safety. 
         [0034]    To achieve this, the disclosure proposes a propulsion assembly for an aircraft comprising a turbine engine in which the turbine engine comprises a rotor and is equipped with an accessory gear box comprising at least one gear mechanically coupled to the rotor. The propulsion assembly also comprises a fairing device comprising an outer annular wall and an inner annular wall that together delimit an internal compartment fitted with an air inlet orifice and an air exhaust orifice. 
         [0035]    According to the disclosure, the propulsion assembly comprises at least one fan unit housed in the internal compartment and comprising a fan propeller and coupling and uncoupling structure for coupling and uncoupling the fan propeller and the gear. 
         [0036]    The fan makes it possible to cool the internal compartment even when the aircraft is moving at low speed on the ground or when it is stopped. 
         [0037]    The disclosure thus limits the dimensions necessary for the air inlet orifice formed in the outer wall of the fairing device. 
         [0038]    In particular, this makes it easier to extinguish a fire within the internal compartment. This helps limiting the required sizing of a fire fighting system that can be installed on the fairing device. 
         [0039]    The disclosure also makes the presence of a dynamic air intake for air inlet superfluous. This also contributes to reducing the ram drag of the fairing device. 
         [0040]    In particular, the lack of a scoop projecting at the air inlet orifice can also reduce the risk of ice formation at this orifice. 
         [0041]    The disclosure also helps reducing the design constraints as regards the position of the air inlet orifice. 
         [0042]    The fan propeller and gear coupling and uncoupling structure help to couple and uncouple these two elements and therefore to start and stop the fan propeller when required. 
         [0043]    In particular, this avoids the need to draw off mechanical energy from the accessory gear box to drive the fan propeller when operation of the fan is not necessary for cooling and ventilation of the internal compartment in which this fan is installed. 
         [0044]    The coupling and uncoupling structure advantageously include a first shaft fixed in rotation to the fan propeller, a second shaft fixed in rotation to the gear of the accessory gear box, and an electromagnetic clutch connecting the first shaft and the second shaft to each other. 
         [0045]    In a first preferred embodiment of the disclosure, the turbine engine is a double flow turbojet (also called “turbofan” or “ducted fan turbine engine”), the outer annular wall forms an external fairing of the turbine engine, and the inner annular wall delimits an annular channel for the bypass air flow of the turbine engine. 
         [0046]    In other words, relative wind flowing around the turbine engine is adjacent to the outer annular wall, while the bypass air flow is adjacent to the inner annular wall. 
         [0047]    In this case, the internal compartment is preferably located axially between an air intake and a thrust inverter that forms part of the fairing device. 
         [0048]    In a second preferred embodiment of the disclosure, the turbine engine is a double flow turbojet, the outer annular wall delimits an annular flow channel of a bypass air flow of the turbine engine, and the inner annular wall delimits a core of the turbine engine. 
         [0049]    In other words, the bypass air flow is adjacent to the outer annular wall, while the inner annular wall surrounds the turbine engine core. Some portions of the inner annular wall may delimit an annular flow channel from a core air flow in the turbine engine. 
         [0050]    In a third preferred embodiment of the disclosure, the turbine engine is a single flow turbojet or an open rotor turbofan or a turboprop, the outer annular wall forms an external fairing of the turbine engine and the inner annular wall delimits a core of the turbine engine. 
         [0051]    In other words, the relative wind flowing around the turbine engine is adjacent to the outer annular wall, while the inner annular wall surrounds the turbine engine core. Some portions of the inner annular wall may delimit an annular flow channel for an air flow inside the turbine engine. 
         [0052]    In general, the propulsion assembly advantageously comprises a control unit to control the coupling and uncoupling structure. 
         [0053]    The control unit is preferably electrically connected to the coupling and uncoupling structure so as to enable electrical control of these means. 
         [0054]    The propulsion assembly advantageously comprises measurement structure configured to measure the air temperature within the internal compartment and to provide the result of this measurement to the control unit. Furthermore, the control unit is preferably configured such that the fan propeller and the gear of the accessory gear box are uncoupled when the temperature measured by the measurement structure is less than a predetermined temperature threshold, and such that the fan propeller and the gear of the accessory gear box are coupled when the temperature measured by the measurement structure is greater than the predetermined temperature threshold. 
         [0055]    Thus, the ventilation may be started as soon as the temperature measured in the compartment reaches the above mentioned temperature threshold. 
         [0056]    The propulsion assembly advantageously can provide information about the rotation speed of the rotor to the control unit, and the control unit is preferably configured such that the fan propeller and the gear of the accessory gear box are uncoupled when the rotation speed of the rotor is greater than a predetermined speed threshold, such that the fan propeller and the gear of the accessory gear box are coupled when the rotation speed of the rotor is less than the predetermined speed threshold. 
         [0057]    Thus, ventilation may be started as soon as the rotation speed of the rotor drops below the above-mentioned speed threshold. Such a situation may correspond to a low speed aircraft displacement phase justifying activation of the ventilation. 
         [0058]    If the propulsion assembly comprises the above mentioned measurement structure and also is equipped and adapted to provide the above mentioned information, the control unit is preferably configured such that the fan propeller and the gear of the accessory gear box are uncoupled when the temperature measured by the measurement structure is less than the predetermined temperature threshold and the rotation speed of the rotor is greater than the predetermined speed threshold, and such that the fan propeller and the gear are coupled when the temperature measured by the measurement structure is greater than the predetermined temperature threshold, or the rotation speed of the rotor is less than the predetermined speed threshold. 
         [0059]    The disclosure also relates to an aircraft, comprising at least one propulsion assembly of the type disclosed above. 
         [0060]    Finally, the disclosure relates to a method of ventilating an internal compartment in a fairing device of a propulsion assembly of the type disclosed above, including coupling of the fan propeller and the gear such that the gear drives the fan propeller so as to generate a ventilation air flow, and the method further including later uncoupling of the fan propeller and the gear such that the gear no longer drives the fan propeller. 
         [0061]    If the propulsion assembly includes the control unit and the measurement structure, the method preferably includes coupling of the fan propeller and the gear of the accessory gear box when the temperature measured by the measurement structure is greater than the predetermined temperature threshold, and uncoupling of the fan and the gear when the temperature measured by the measurement structure is less than the predetermined threshold. 
         [0062]    If the propulsion assembly includes the control unit and is configured to provide the information noted, the method preferably includes coupling of the fan propeller and the gear of the accessory gear box when the rotation speed of the rotor is less than the predetermined speed threshold, and uncoupling of the fan propeller and the gear when the rotation speed of the rotor is greater than the predetermined speed threshold. 
         [0063]    Finally, if the propulsion assembly comprises the above mentioned measurement structure and also configured to provide the above mentioned information, the method preferably includes uncoupling of the fan propeller and the gear when the temperature measured by the measurement structure is less than the predetermined temperature threshold and the rotor rotation speed is greater than the predetermined speed threshold, and coupling of the fan propeller and the gear when the temperature measured by the measurement structure is greater than the predetermined temperature threshold or the rotor rotation speed is less than the predetermined speed threshold. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0064]    The disclosure will be better understood and other details, advantages and characteristics of the disclosure will appear clear after reading the following description given as non-limitative examples with reference to the appended drawings, in which: 
           [0065]      FIG. 1  described above is a partial diagrammatic axial sectional view of a known type of propulsion assembly; 
           [0066]      FIG. 2  is a partial diagrammatic axial sectional view of a propulsion assembly according to a first preferred embodiment of the disclosure; 
           [0067]      FIG. 2   a  is a larger scale view of a fan forming part of a fairing device of the propulsion assembly in  FIG. 2 ; 
           [0068]      FIG. 3  is a partial diagrammatic axial sectional view of a propulsion assembly according to a second preferred embodiment of the disclosure; 
           [0069]      FIG. 4  is a partial diagrammatic axial sectional view of a propulsion assembly according to a third preferred embodiment of the disclosure. 
       
    
    
       [0070]    In these figures, identical references may refer to identical or similar elements. 
       DETAILED DESCRIPTION 
       [0071]      FIG. 2  shows a propulsion assembly  10  according to a first embodiment of the disclosure similar to that in  FIG. 1 , but in which a fan  70  is housed in the internal compartment  28  of the external fairing device  14 , aft from the air inlet orifice  42 . 
         [0072]    The fan  70  comprises a fan propeller  74 , a first shaft  76  fixed to the fan propeller  74 , an electromagnetic clutch  78 , a second shaft  80  carrying a first gear  82  engaged with a rotor shaft  84  of an electric motor  86  and a second gear  88  engaged with a gear  89  forming part of the accessory gear box  36  and driven in rotation by the intermediate shaft  40 . 
         [0073]    The first shaft  76 , the electromagnetic clutch  78 , the second shaft  80  and the second gear  88  form “coupling and uncoupling structure” for coupling and uncoupling the fan propeller  74  and the gear  89  of the accessory gear box  36 , in the terminology of the disclosure. 
         [0074]    The electromagnetic clutch  78 , very diagrammatically shown in  FIG. 2   a , comprises a first rotating part  90  fixed in rotation to the first shaft  76 , and a second rotating part  92  fixed in rotation to the second shaft  80 . In a manner known in itself, the electromagnetic clutch  78  includes electrical control for alternatively coupling and uncoupling the two rotating parts  90  and  92 . More precisely, the two rotating parts  90  and  92  are coupled by being forced towards each other, under the effect of a return force, preferably a mechanical force, until they come into contact with each other so as to rotate at unison. Conversely, the two rotating parts  90  and  92  are uncoupled by being forced away from each other, under the effect of a magnetic force in opposite direction, until the two rotating parts are no longer fixed to each other in rotation. 
         [0075]    The electric motor  86  is used as a source of electric current to control the electromagnetic clutch  78 . To achieve this, the rotor shaft  84  of the electric motor  86  is driven in rotation by the first gear  82  carried by the second shaft  80  so as to induce an electric current powering the electromagnetic clutch  78 . 
         [0076]    As a variant, the electric motor may be integrated into the second shaft  80 . In other words the rotor of the electric motor may be formed directly by the second shaft  80 . In such case the stator of the electric motor surrounds this second shaft  80 . 
         [0077]    As another variant, the electromagnetic clutch  78  may be connected to a general electricity network of the turbojet powered by a main alternator of the turbojet, sometimes called IDG (Integrated Drive Generator), and possibly by an Auxiliary Power Unit (APU) of this turbojet. 
         [0078]    The propulsion unit  10  comprises a control unit  94  capable of switching the state of the electromagnetic clutch  78  and therefore controlling rotation or stopping of the fan propeller  74  of the fan  70 . 
         [0079]    This control unit  94  may be a multi-functional unit currently called the Engine Control Unit (ECU), or as a variant an electronic unit dedicated to control of the fan  70 . 
         [0080]    In both cases, the control unit  94  is preferably coupled to measurement structure comprising a sensor  96  to measure the air temperature inside the internal compartment  28 . 
         [0081]    Furthermore, the control unit  94  is preferably coupled to the information providing portion  98  providing information about the rotation speed of the rotor  38  to the control unit  94 . 
         [0082]    This control unit  94  is configured such that the two rotating parts  90  and  92  of the electromagnetic clutch  78  are:
       uncoupled when the temperature measured by the sensor  96  is less than a predetermined temperature threshold and the rotation speed of the rotor  38  provided by the information providing portion  98  is greater than a predetermined speed threshold,   coupled when the measured temperature exceeds the predetermined temperature threshold or the rotation speed of the rotor  38  is less than the predetermined speed threshold.       
 
         [0085]    Thus, when the measured temperature exceeds the above mentioned temperature threshold, the fan propeller  74  of the fan  50  is driven in rotation and it increases the ventilation of the internal compartment  28  by forced convection and therefore improves cooling of the systems contained inside the internal compartment  28 . The same applies when the rotation speed of the rotor  38  is less than the predetermined speed threshold, which can occur when the flight is in a low speed phase or is taxiing, which requires action of the fan. 
         [0086]    On the other hand, when the measured temperature is less than the above mentioned temperature threshold and the rotation speed of the rotor  38  is greater than the predetermined speed threshold, the blade  74  of the fan  70  is not driven in rotation to limit the ram drag on the air inlet orifice  42  and the energy consumption of the fan  50 . 
         [0087]    Note that the information providing portion  98  may include a dedicated speed sensor connected to the control unit  94  to measure the rotation speed of the rotor. As a variant, the information providing portion  98  may be composed of a connection that may be connected to an electronic unit fitted on the airframe of an aircraft to receive information about the engine speed or the flight phase corresponding to the position of flight control devices installed in the cockpit. In this case the predetermined speed threshold may correspond to a minimum engine speed imposed for a given flight phase, for example the cruising phase. 
         [0088]    Finally, the control unit  94  is configured such that under failsafe conditions, the two rotating parts  90  and  92  of the electromagnetic clutch  78  are coupled, such that the fan  70  then ventilates the internal compartment  28 . To achieve this, the electromagnetic clutch  78  is designed such that if there is no electric power supply to it, its two rotating parts  90  and  92  are coupled to each other. 
         [0089]    In operation, the internal compartment  28  may thus be ventilated by a method including:
       coupling of the fan propeller  74  and gear of the accessory gear box  36 ,  36 ′ when the temperature measured by the measurement structure  96  is greater than the predetermined temperature threshold or when the rotation speed of the rotor  38  provided by the information providing portion 98  is less than the predetermined speed threshold, and   uncoupling of the fan propeller  74  and the gear  89 ,  89 ′ when the temperature measured by the measurement structure is less than the predetermined threshold and the rotation speed of the rotor  38  is greater than the predetermined speed threshold.       
 
         [0092]    The disclosure according to the first embodiment thus discloses a simple and efficient way of ventilating the internal compartment  28  of the external fairing device  14 , that remains efficient when the aircraft is travelling at low speed on the ground or when it is stopped. 
         [0093]    The disclosure can thus limit the required dimensions for the air inlet orifice  42  formed in the outer wall  16  of the external fairing device  14 . In particular, this makes it easier to extinguish a fire inside the internal compartment  28  and therefore limits the size of the fire fighting system required for the external fairing device  14 . 
         [0094]    The disclosure also makes the dynamic nature of the air intake formed by the air inlet orifice  42  superfluous. In other words, the outer wall  16  does not need a profiled portion and scoop such that the air inlet orifice is essentially a static air intake. The result is a reduction in the aerodynamic drag of the external fairing device  14 . The lack of a scoop also reduces the risk of ice accumulating at the air inlet orifice  42 . 
         [0095]    The disclosure can generally give better control of the ventilation air flow  46 , which in particular limits the ram drag during flight. 
         [0096]      FIG. 3  shows a propulsion assembly  10  according to a second embodiment of the disclosure similar to that in  FIG. 1 , but in which a fan  100  is housed in the internal compartment  54  of the internal fairing device  48 , aft from the air inlet orifice  56  of the fairing device. 
         [0097]    In the example shown, the fan  100  is similar to the fan  70  in  FIG. 2 , and is also coupled to a gear of the accessory gear box, which in this case is housed in the internal compartment  54  of the internal fairing device  48 . Note that the size is reduced thanks to the circumferential offset of the fan  100  from the accessory gear box around the longitudinal axis  72  of the turbojet. Due to the offset the accessory gear box is not visible in the section plane in  FIG. 3 . 
         [0098]    Operation of the fan  100  is similar to operation of the fan  70  described above. 
         [0099]    The disclosure according to the second embodiment thus discloses a simple and efficient way of ventilating the internal compartment  54  of the internal fairing device  48 , which is particularly advantageous for a turbojet with a high dilution ratio. 
         [0100]    The disclosure according to this second embodiment also has the advantages of the first embodiment related to the fire risk, but in this case inside the internal compartment  54  of the internal fairing device  48 . 
         [0101]    Note that the two embodiments disclosed above may be combined to provide a turbojet in which each of the internal compartments  28  and  54  of the external fairing device  14  and the internal fairing device  48  respectively is provided with a fan. In both cases, the two fans may each be coupled to the compressor rotor  38  mechanically. 
         [0102]      FIG. 4  shows a propulsion assembly  10 ′ according to a third embodiment of the disclosure, in which the turbine engine is a turboprop  12 ′ and generally comprises a propeller  30 ′ and a core  26 ′ for example including an intermediate pressure compressor  110 , a high pressure compressor  112 , a combustion chamber  114 , a high pressure turbine  116 , an intermediate pressure turbine  118  and a low pressure turbine  120 . The propeller  30 ′ is coupled to a reduction device  122  that is itself coupled to a rotor shaft  124  of the intermediate pressure compressor  110 . 
         [0103]    The core  26 ′ of the turboprop is surrounded by a fairing device  48 ′ comprising an outer annular wall  50 ′ that provides fairing around the propulsion assembly, and an inner annular wall  52 ′ that surrounds a flow channel directing the core air flow  25  supplying the turboprop core  26 ′. The outer annular wall  50 ′ and the inner annular wall  52 ′ together delimit an internal compartment  54 ′. 
         [0104]    The outer annular wall  50 ′ is provided with an air inlet orifice  56 ′, and an air exhaust orifice  58 ′ arranged on the downstream side of the air inlet orifice  56 ′ diametrically opposite it. 
         [0105]    Furthermore, an accessory control box  36 ′ is housed in the internal compartment  54 ′. 
         [0106]    In a manner similar to that described above, the propulsion assembly  10 ′ comprises a fan  100 ′ housed in the internal compartment  54 ′ so as to generate a ventilation air flow  46 ′ by forced convection. 
         [0107]    In the example shown, the fan  100 ′ is similar to the fan  100  in  FIG. 3 , and is also coupled to a gear  89 ′ of the accessory gear box  36 ′. 
         [0108]    Therefore operation of the fan  100 ′ is similar to operation of the fan  100  disclosed above. 
         [0109]    The disclosure according to this third embodiment thus has the same advantages as those disclosed above with reference to the second embodiment.