Nacelle for a propulsion unit of an aircraft comprising an access space enclosed by a tangential clamping cover

Abstract

A nacelle (24) for an aircraft propulsion unit, the nacelle comprising: an air inlet cowl portion (34) and an intermediate section (36) comprising a fixed removable cover portion (60) defining an access space (80) between a forward end (65) of the cover portion and an outer aft end (52) of the air inlet cowl portion. The intermediate section comprises: an annular row of mutually spaced apart connecting members (82) rigidly connecting the outer aft end of the air inlet cowl portion to the forward end of the cover portion to transmit longitudinal forces; and an intermediate cowl portion (84) extending around the connecting members between the air inlet cowl portion and the cover portion to enclose the access space and form aerodynamic continuity with the air inlet cowl portion and the cover portion. The intermediate cowl portion is formed by at least one strip portion (86) held in place by tangential clamping of circumferential ends (86A, 86B) of the strip portion.

Description

Technical Field

[0001] The present invention relates to the field of aircraft propulsion units, and more particularly to nacelles of the type in which the middle section of the nacelle includes a removable fixed cover, that is, in order to provide access to the interior of the propulsion unit, it is necessary to remove the cover which is rigidly attached to at least one other component of the nacelle by an attachment member. Background Technology

[0002] Aircraft propulsion unit nacelles typically have a tubular structure comprising, from upstream to downstream: an upstream section formed by an air intake shroud configured to separate the airflow entering the turbine engine and the airflow bypassing the propulsion unit during operation; an intermediate section configured to surround a fan around the turbine engine; and a downstream section including a thrust reverser and configured to surround a gas generator around the turbine engine. The shroud should be understood as a single cover or an assembly of multiple covers.

[0003] In some nacelles, the central section cover (often referred to as the fan cover) is hinged to the nacelle's fixed structure or the propulsion unit's mast fixed structure, thus allowing it to pivot from a closed position to an open position via a motion known as "butterfly motion," enabling access to the propulsion unit's interior, for example, for maintenance operations. Typically, these nacelles are large, costly, and their opening involves high loads.

[0004] In other nacelles, particularly when it is desirable to avoid the aforementioned drawbacks, the cover of the intermediate section is rigidly attached to at least one other component of the nacelle (particularly the air intake mask) by an attachment member, which must be removed to access the interior of the propulsion unit. In this case, the cover can be defined as both "fixed" and "movable". The present invention relates to nacelles including such a cover.

[0005] Document FR3004700 discloses an example of a nacelle with an elongated air inlet lip and a movable fixed cover.

[0006] In this nacelle, the air intake mask has an inner rear end configured to be rigidly and removably attached to an annular flange of the turbine engine fan housing, and the air intake mask has an outer rear end to which the front end of the removable fixing cover is attached by attachment through members (e.g., screws, right-angle swivel screws, or screws with a reduced number of threads). The attachment through members are distributed around the axis of the nacelle, and the number of attachment through members approximately ensures precise alignment between the components and minimizes non-uniformity.

[0007] When it is necessary to remove air from the fan housing, the fact that the annular flange must be accessed necessitates the removal of all attachments and through-members of the cover. Therefore, this operation is time-consuming and costly. Summary of the Invention

[0008] In particular, the purpose of this invention is to provide a simple, economical and effective solution to the above problems.

[0009] Therefore, the present invention proposes a nacelle for an aircraft propulsion unit, the nacelle comprising, from front to back:

[0010] - An air intake mask has an inner rear end and an outer rear end, the inner rear end being configured to be rigidly and removably attached to the fan housing of the turbine engine.

[0011] - The intermediate section includes fixed and removable covers distributed along the axis of the nacelle; and

[0012] - Rear section;

[0013] According to the invention, the cover has front ends, each front end arranged axially facing the outer rear end of the air inlet mask and defining an approach space between the front ends of the cover and the outer rear end of the air inlet mask at a distance from the outer rear end of the air inlet mask, and the intermediate section further includes:

[0014] - A ring of spaced-apart connecting parts, which rigidly connect the outer rear end of the air inlet mask to the front end of the cover, thereby transmitting longitudinal force between the air inlet mask and the cover; and

[0015] - An intermediate cover extends annularly around the connecting member between the air inlet cover and the cover to enclose the access space and form aerodynamic continuity with the air inlet cover and the cover. The intermediate cover is formed by at least one strip, which is held in place by tangential clamping at the circumferential end of the at least one strip.

[0016] When access to the internal volume of the air intake mask is required, it is simply necessary to release the tangential clamps at the ends of one or more strips forming the intermediate mask, which is much faster and easier than removing multiple annular rows of attachment members to the cover (as is necessary for nacelles of known types).

[0017] Once the intermediate cover is removed, the access space is uncovered, allowing the operator to access the internal volume of the air intake cover to, for example, act on the attachment device that connects the inner rear end of the air intake cover to the fan housing.

[0018] Therefore, the air intake cover can be removed, or conversely, installed on the turbine engine, and, more generally, the internal volume can be accessed without first removing the cover of the middle section.

[0019] The present invention takes advantage of the fact that, due to the limited extension and therefore the limited mass of the cover, attaching one or more strips forming the cover is not critical to the safety of the aircraft in flight, which makes it possible that the separation of such strips during flight will not pose a risk of serious damage in the event of a collision with the aircraft's units.

[0020] Therefore, the cover preferably has an axial extension of less than 30 cm, and more preferably an axial extension between 15 cm and 25 cm (e.g., 20 cm).

[0021] In a preferred embodiment of the invention, the air inlet mask portion includes a first edge that is radially offset inward, and the front end portion of the intermediate mask portion rests on the first edge.

[0022] In a preferred embodiment of the invention, each cover portion includes a second edge that is radially offset inward, and the rear end portion of the intermediate cover portion rests on the second edge.

[0023] In a preferred embodiment of the invention, at least one strip-shaped portion includes two strip-shaped portions arranged on both sides of the central vertical plane of the nacelle.

[0024] In a preferred embodiment of the invention, tangential clamping of at least one strip portion is performed by at least one resiliently biased removable attachment member.

[0025] In a preferred embodiment of the invention, the air inlet mask portion includes a clamping structure, on which at least one strip-shaped portion is tangentially clamped.

[0026] In a preferred embodiment of the invention, the connecting member is connected to the outer rear end of the air inlet mask part and the front end of the cover part by a removable attachment through member.

[0027] In a preferred embodiment of the invention, the rear section includes a thrust reverser, the thrust reverser including a deflection grille movable between a forward direct thrust position and a retracted thrust reverse position, and wherein the cover covers at least the front portion of the deflection grille in the forward direct thrust position.

[0028] The present invention also relates to an aircraft propulsion unit, the aircraft propulsion unit comprising:

[0029] - A turbine engine, comprising a fan and a fan housing surrounding the fan; and

[0030] - A nacelle of the type described above, which surrounds the turbine engine, with the inner rear end of the nacelle's air intake mask rigidly and removably attached to the turbine engine's fan housing.

[0031] In a preferred embodiment of the invention, the fan housing includes a clamping structure on which at least one strip-shaped portion is tangentially clamped. Attached Figure Description

[0032] The invention will be better understood by reading the following description, which is given by way of non-limiting example and with reference to the accompanying drawings, and other details, advantages and features will become apparent:

[0033] - Figure 1 This is a partial schematic diagram of the axial cross-section of the aircraft's propulsion unit;

[0034] Figure 2 is a partial schematic half-view of a larger-scale axial section of a propulsion unit for a known type of aircraft.

[0035] - Figure 3 is a schematic perspective view of the propulsion unit of Figure 2, wherein the fixed and removable type cover has been removed;

[0036] - Figure 4 This is a view similar to Figure 2, showing the propulsion unit according to a preferred embodiment of the present invention;

[0037] - Figure 5 yes Figure 4 A larger-scale view of a portion shows the fan housing of the propulsion unit, as well as the middle section of the nacelle and the air intake mask.

[0038] - Figure 6 yes Figure 5 A larger-scale view of a portion shows the middle section of the nacelle and the air intake mask section. Figure 9 The cross section in the VI-VI plane;

[0039] - Figure 7 It is similar to Figure 6 In Figure 9 A view of the section in plane VII-VII;

[0040] - Figure 8 yes Figure 4 A partial schematic diagram of the propulsion unit;

[0041] - Figure 9 It is similar to Figure 8 The view shows the strip-shaped portion of the middle cover that partially forms the middle section of the nacelle, and shows the proximity space between the front end of the cover and the outer rear end of the air inlet cover.

[0042] - Figure 10 It is similar to Figure 9 According to another perspective;

[0043] - Figure 11 yes Figure 4 A partial schematic top view of the propulsion unit, in which the approach space can be seen;

[0044] - Figure 12 It is similar to Figure 9 The view further illustrates the strip-shaped portion;

[0045] - Figure 13 yes Figure 4 The propulsion unit along Figure 12 A partial schematic diagram of the cross-section of the XIII-XIII plane shows the tangential clamping device of the intermediate cover;

[0046] - Figure 14 It is similar to Figure 13 The view shows an alternative embodiment of the tangential clamping device.

[0047] In all these figures, the same reference numerals may denote the same or similar elements. Detailed Implementation

[0048] Figure 1 An aircraft propulsion unit 8 is shown, which includes, for example, a dual-flow, dual-body type turbine engine 10. The dual-flow, dual-body type turbine engine typically includes a fan 12, which is configured to draw in an airflow F1. Downstream of the fan, the airflow is divided into a main flow F2 that flows in a main flow channel (hereinafter referred to as the main path PV) located within the core of the turbine engine, and a secondary flow F3 that bypasses the core in a secondary flow channel (hereinafter referred to as the secondary path SV).

[0049] The core of a turbine engine typically includes a low-pressure compressor 14, a high-pressure compressor 16, a combustion chamber 18, a high-pressure turbine 20, and a low-pressure turbine 22.

[0050] The individual rotors of the high-pressure compressor and the high-pressure turbine are connected by a shaft called the "high-pressure shaft," while the individual rotors of the low-pressure compressor and the low-pressure turbine are connected by a shaft called the "low-pressure shaft" in a known manner.

[0051] The turbine engine is guided by a nacelle 24 surrounding the secondary passage SV. Furthermore, the turbine engine rotor is rotatably mounted about the turbine engine's axis, which coincides with the axis of the nacelle 24 within the propulsion unit 8. These two axes are indistinguishably indicated in this specification by reference numeral 28.

[0052] Throughout this specification, the axial direction X is the direction of axis 28, the vertical direction Z is the direction orthogonal to the axial direction X and oriented according to the vertical direction when the propulsion unit 8 is mounted on an aircraft located on the ground, and the lateral direction Y is orthogonal to the aforementioned two directions. Furthermore, the radial direction R and the circumferential direction C, or the azimuth direction, are defined with reference to axis 28, while the "upstream" and "forward" directions, and the "downstream" and "rearward" directions, are defined with reference to the overall gas flow in the turbine engine.

[0053] The turbine engine includes a compressor housing 30 (shown separately in Figure 2) arranged axially between the low-pressure compressor 14 and the high-pressure compressor 16. In the non-limiting case of a twin-body turbine engine, this compressor housing 30 is sometimes referred to as an intermediate housing.

[0054] Referring to Figure 2, which illustrates such a propulsion unit according to a known configuration, the compressor housing 30 supports a fan housing 32 arranged upstream of the compressor housing surrounding the fan 12. The fan housing 32 includes an annular flange 33 at its upstream end.

[0055] In addition, the nacelle 24 includes, from front to back, an air intake mask section 34, a middle section 36, and a rear section 38.

[0056] The air inlet lip 34 primarily comprises an outer wall 40 having an overall C-shaped cross-section, the outer wall having an upstream convex surface and being configured to separate the airflow entering the turbine engine 10 and the airflow bypassing the propulsion unit 8 during operation. Therefore, the outer wall 40 has two opposing end portions defining an inner shell portion 42 and an outer shell portion 44, which are interconnected by an annular intermediate portion 46 with a convex cross-section to form an air inlet lip. Thus, the outer wall 40 defines an internal volume 48 of the air inlet lip 34, which forms the front portion of the internal volume of the nacelle 24. The inner shell portion 42 has a rear end portion, for example, forming an acoustic panel 42A.

[0057] The inner shell portion 42 defines the inner rear end portion 50 of the air inlet mask portion 34 at the rear end portion of the inner shell portion, while the outer shell portion 44 defines the inner rear end portion 52 of the air inlet mask portion 34 at the rear end portion of the outer shell portion.

[0058] The inner rear end 50 is rigidly and removably attached to the annular flange 33 of the fan housing 32, for example by one or more annular rows of removable attachment through members 53 (e.g., bolts).

[0059] As an illustration, the air intake mask part 34 also includes an annular front partition 54, which connects the front region of the inner shell part 42 to the front region of the outer shell part 44.

[0060] In the example shown, the middle portion 46 or air inlet lip and the outer shell portion 44 are integrated. In other words, the air inlet lip is of an elongated type, meaning that the air inlet lip extends to the outer rear end 52 of the air inlet mask portion 34.

[0061] Alternatively, the intermediate portion 46 or the air inlet lip and the outer shell portion 44 may be formed by different covers assembled with each other. In this case, the air inlet lip portion 34 also includes an annular rear partition that connects the rear region of the inner shell portion 42 to the rear region of the outer shell portion 44.

[0062] The middle section 36 of the nacelle includes a fixed and removable cover 60 distributed around the axis 28 of the nacelle. The cover defines the middle portion 62 of the internal volume of the nacelle 24 externally. The middle portion of the internal volume of the nacelle is located downstream of the internal volume 48 of the air inlet mask 34 around the fan housing 32.

[0063] The intermediate section 36 also includes an annular main bulkhead 64, which extends within the intermediate portion 62 of the internal volume of the nacelle 24 and connects the fan housing 32 to the cover 60.

[0064] The cover 60 rigidly connects the front end 65 of each cover to the outer rear end 52 of the air inlet mask 34. For aerodynamic continuity, the front end 65 of the cover and the outer rear end 52 of the air inlet mask 34 are attached, for example, to a shell portion that is typically added to the inner surface of these elements by a removable row of attachment through members 66 (e.g., screws). The cover 60 has a corresponding rear portion 68 that is typically attached to the main partition 64 by a removable row of attachment through members 70 (e.g., screws).

[0065] The rear section 38 of the nacelle includes a thrust reverser, for example, comprising a deflection grid movable from front to rear to switch from a retracted configuration for operating the propulsion unit in direct thrust mode to an deployed configuration for operating the propulsion unit in thrust-reversing mode. As shown in FIG2, for example, the grid 72 of such a thrust reverser is wholly or partially surrounded by the rear portion 68 of the cover 60 in the retracted configuration.

[0066] The fact that access to the annular flange 33 of the fan housing 32 is required to remove air intake 34 necessitates the removal of all attachment members 66 and 70 of the cover 60 to allow access to the internal volume of the nacelle, as shown in Figure 3. This operation is time-consuming and costly.

[0067] To solve this problem, equipment is installed in Figures 4 to 14The nacelle 24 in the propulsion unit shown is configured such that the cover 60 has a front end 65, each front end being arranged axially facing the outer rear end 52 of the air inlet mask 34 and defining an approach space 80 between the front end 65 of the cover and the outer rear end 52 of the air inlet mask at a distance from the outer rear end of the air inlet mask. Figures 6 to 12 The “access space” should be understood as a space with sufficient axial extension to allow an operator to pass their arm through, enabling the operator’s arm to act on the removable attachment through member 53, which connects the inner rear end 50 of the air intake mask portion 34 to the annular flange 33 of the fan housing 32. An axial extension of 20 cm is considered satisfactory for this purpose, although in some preferred embodiments of the invention, an axial extension more typically between 15 cm and 30 cm is possible.

[0068] In addition, the middle section 36 of the nacelle includes an annular row of spaced-apart connecting parts 82. Figure 6 and Figures 9 to 12 The spaced-apart connecting members rigidly connect the outer rear end portion 52 of the air inlet mask 34 to the front end portion 65 of the cover 60, thereby transmitting longitudinal force between the air inlet mask 34 and the cover 60. In some embodiments, the connecting members 82 also facilitate the transmission of radial loads and / or torques between the air inlet mask 34 and the cover 60.

[0069] The connecting member 82 is advantageously attached to the outer rear end 52 of the air inlet mask portion 34 on one hand and to the front end 65 of the cover portion 60 on the other hand via a removable attachment through member 83. Figure 6 For this purpose, each of the connecting parts 82 has an opposing end, which is respectively added to the inner surface of the outer rear end 52 of the air inlet mask 34 and the front end 65 of the inner surface of the cover 60.

[0070] In addition, the intermediate section 36 of the nacelle includes an intermediate cover section 84. Figure 6 and Figure 7 The intermediate cover extends between the air inlet cover 34 and the cover 60 around the connecting member 82 in an annular arrangement to close the access space 80 and form aerodynamic continuity with the air inlet cover 34 and the cover 60.

[0071] The intermediate cover 84 consists of one or more strip-shaped sections (e.g., two strip-shaped sections 86 arranged on both sides of the intermediate vertical plane P of the nacelle 24). Figure 8 ))form.

[0072] The strip-shaped portion or each strip-shaped portion 86 passes through the circumferential ends 86A, 86B of the strip-shaped portion or each strip-shaped portion. Figure 12The tangential clamping holds it in place, which will become clearer and more apparent in the following text.

[0073] Reference Figure 6 and Figure 7 The air inlet mask portion 34 includes a first edge 90 that is radially offset inward, and the front end portion 92 of the intermediate mask portion 84 rests on the first edge. The first edge 90 is defined to extend beyond the outer rear end portion 52 of the air inlet mask portion 34 in a rearward direction.

[0074] Similarly, the cover 60 includes a corresponding second edge 94 that is radially offset inward, and the rear end portion 96 of the intermediate cover 84 rests on the second edge. The second edge 94 is defined to extend beyond the front end portion 65 of the cover 60 in a forward direction.

[0075] Therefore, aerodynamic continuity can be optimally ensured on the one hand between the air inlet mask 34 and the intermediate mask 84, and on the other hand between the intermediate mask 84 and the cover 60.

[0076] The strip-shaped portion 86 is tangentially clamped in the clamping structure 100. Figure 12 and Figure 13 The clamping structure is supported, for example, by the air intake mask part 34.

[0077] In the example shown, there are two such clamping structures 100 arranged in the upper part of the nacelle 24, symmetrically located on both sides of the intermediate vertical plane P (one of the two clamping structures can be seen in the figure), and two other similar clamping structures arranged in the lower part of the nacelle 24, also symmetrically located on both sides of the intermediate vertical plane P.

[0078] Two clamping structures 100 arranged in the upper portion of the nacelle 24 are covered, for example, by an upper longitudinal shield strip 102, which extends from the outer rear end 52 of the annular cover and has a rear end flush with the corresponding rear end 104 of the cover 60. Similarly, two clamping structures arranged in the lower portion of the nacelle 24 are covered, for example, by a lower longitudinal shield strip 106, which extends rearward from the outer rear end 52 of the annular cover and has a rear end flush with the corresponding rear end 104 of the cover 60. The longitudinal shield strip is attached, for example, to the clamping structure 100.

[0079] Each strip 86 of the intermediate cover portion 84 includes a retainer 110 at each of the circumferential ends 86A, 86B of the strip 86, which is added to the inner surface of the strip 86, and at least one removable attachment member 112 (e.g., a bolt) is restrained in the retainer.

[0080] The tangential clamping of each strip 86 is performed by inserting each of the removable attachment members 112 connected to the circumferential end of the strip into an opening provided in the corresponding clamping structure 100 at the top and bottom positions for this purpose, and then screwing a nut 114 (or any other similar device) into each of the removable attachment members 112, wherein an elastic biasing device 116 (e.g., a spring or a Bass washer) is inserted between the nut 114 and the corresponding clamping structure 100, such that the elastic biasing device 116 elastically biases the corresponding end of the strip in the direction of the clamping structure 100 under consideration.

[0081] Figure 14 An alternative embodiment is shown, in which the clamping structure 100 is supported by the fan housing 32.

[0082] Alternatively, the number of strips forming the intermediate cover portion 84 and the number of clamping structures may differ from those described above.

[0083] For example, the two clamping structures 100 at the top position can be combined to form a single integral structure. The same applies to the two clamping structures 100 at the bottom position.

[0084] In addition, apart from the area corresponding to (if applicable) the longitudinal protective strip 102, the intermediate cover 84 may be formed by a single strip extending around the entire axis 28.

[0085] In this case, the tangential clamping of the strip forming the intermediate cover portion 84 can be performed directly between the two opposite ends of the strip without involving any fixed clamping structure.

[0086] As an alternative, a combination of one or more clamping structures supported by the air inlet mask 34 and one or more other clamping structures supported by the fan housing 32 can still be provided.

[0087] In any case, when access to the annular flange 33 of the fan housing 32 is required, it is simply necessary to release the tangential clamps on the ends of one or more strips 86 forming the intermediate cover portion 84, and simply to remove one or more strips 86, which is much faster and easier than removing multiple annular rows of attachment members of the cover portion 60 (as is necessary for nacelles of known types).

[0088] In the example shown, this only requires removing several removable attachment members 112 that ensure axial clamping of the ends of the strip 86.

[0089] Once the intermediate cover 84 is removed, the access space 80 becomes visible, allowing the operator to access the internal volume of the nacelle and, in particular, the annular flange 33 of the fan housing 32, to act, for example, on the removable attachment through member 53 that connects the inner rear end 50 of the air intake cover 34 to the annular flange 33 of the fan housing 32.

[0090] When it is necessary to remove the air inlet mask 34, the procedure also requires the removal of the connecting member 82, or at least the separation of the connecting member from the outer rear end 52 of the air inlet mask 34. The number of these connecting members (which depends only on the level of the connecting force to be transmitted through these members) can be relatively moderate, such that the separation or removal of these members involves far fewer operations for removing the attachment members than the number of operations required for removing the cover of the intermediate section of a known type of nacelle.

[0091] Therefore, the air intake mask 34 can be removed without first removing the cover 60, or conversely, installed on other corresponding parts of the nacelle.

[0092] The present invention utilizes the fact that, due to the limited extension and therefore the limited mass of the intermediate cover 84, attaching one or more strips 86 forming the cover 84 is not critical for the safety of the aircraft in flight, making, for example, the tangential clamping proposed in the present invention acceptable. For this purpose, the intermediate cover 84 preferably has an axial extension of less than 30 cm.

Claims

1. A nacelle (24) for an aircraft propulsion unit, the nacelle comprising, from front to back: - An air inlet mask (34) having an inner rear end (50) and an outer rear end (52), the inner rear end being configured to be rigidly and removably attached to the fan housing (32) of the turbine engine. - Intermediate section (36), said intermediate section including fixed and removable covers (60) distributed around the axis (28) of the nacelle; and - Rear section (38); The cover (60) is characterized in that it has a front end, each front end being arranged axially facing the outer rear end (52) of the air inlet mask (34) and defining an approach space (80) between the front end (65) of the cover and the outer rear end (52) of the air inlet mask at a distance from the outer rear end of the air inlet mask. Furthermore, the intermediate segment (36) also includes: - A ring of spaced-apart connecting parts (82) that rigidly connect the outer rear end (52) of the air inlet mask (34) to the front end (65) of the cover (60), thereby transmitting longitudinal force between the air inlet mask and the cover; and - Intermediate cover (84), which extends annularly around the connecting member (82) between the air inlet cover (34) and the cover (60) to close the access space (80) and form aerodynamic continuity with the air inlet cover and the cover, the intermediate cover (84) being formed of at least one strip (86) which is held in place by tangential clamping of the circumferential ends (86A, 86B) of the at least one strip (86).

2. The nacelle according to claim 1, wherein, The air intake mask portion (34) includes a first edge (90) that is radially offset inward, and the front end portion (92) of the intermediate mask portion (84) rests on the first edge.

3. The nacelle according to claim 1 or 2, wherein, Each of the cover portions (60) includes a second edge (94) that is radially offset inward, and the rear end portion (96) of the intermediate cover portion (84) rests on the second edge.

4. The nacelle according to claim 1 or 2, wherein, The at least one strip (86) includes two strips (86) arranged on both sides of the central vertical plane (P) of the nacelle.

5. The nacelle according to claim 1 or 2, wherein, The tangential clamping of the at least one strip (86) is performed by at least one resiliently biased removable attachment member (112).

6. The nacelle according to claim 1 or 2, wherein, The air intake mask portion (34) includes a clamping structure (100) on which the at least one strip portion (86) is tangentially clamped.

7. The nacelle according to claim 1 or 2, wherein, The connecting member (82) is connected to the outer rear end (52) of the air inlet mask (34) on one hand and to the front end (65) of the cover (60) on the other hand via a removable attachment through member (83).

8. The nacelle according to claim 1 or 2, wherein, The rear section (38) includes a thrust reverser comprising a deflector grille (72) movable between a forward direct thrust position and a retracted thrust reverse position, wherein the cover (60) covers at least a front portion of the deflector grille (72) in the forward direct thrust position.

9. A propulsion unit (8) for an aircraft, the propulsion unit comprising: - Turbine engine (10), the turbine engine including a fan (12) and a fan housing (32) surrounding the fan; as well as - The nacelle (24) according to any one of claims 1 to 8 surrounds the turbine engine (10), and the inner rear end (50) of the air intake mask (34) of the nacelle is rigidly and removably attached to the fan housing (32) of the turbine engine.

10. The propulsion unit according to claim 9, wherein, The fan housing (32) includes a clamping structure (100) on which the at least one strip (86) is tangentially clamped.

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