Turbofan testing machine including a turbofan thrust measurement balance

Abstract

Turbofan testing machine comprising a turbofan thrust measuring balance. One aspect of the invention relates to a fixed part (30) of a turbofan tested on a test machine (2), comprising: A primary part (300) A secondary part (302) A primary flow duct (308), A hub (310) comprising: a cylindrical body (3100) fixed to a thrust measuring balance (24) of the test machine, a hub arm (3102) extending from the cylindrical body (3100) and passing through the duct (308), An isolation deflector (312) of the hub arm located in the duct (308), positioned between the cylindrical body (3100) and the secondary internal casing (302i), the isolation deflector surrounding the hub arm (3102) and being fixed to a fixed fairing (20) of the test machine (2). Figure to be published with the abbreviation: Figure 3.

Description

Title of the invention: Turbofan testing machine comprising a turbofan thrust measurement balance. TECHNICAL FIELD OF THE INVENTION

[0001] The technical field of the invention is that of test machines for aircraft turbofans and more specifically that of balances for measuring the thrust of turbofans.

[0002] The present invention relates to a fixed part of a turbofan for testing, a method of mounting and an assembly comprising a test machine and the fixed part of the turbofan. TECHNOLOGICAL BACKGROUND OF THE INVENTION

[0003] Classically, a test machine is an installation in which engines and in particular turbojets are tested in operation, especially during the development phase of the latter.

[0004] For example, a test machine can be used to determine the ability of a fan of a turbofan engine to produce a counter-thrust.

[0005] Fig. 1 is a schematic representation of an axial section of an assembly 1 comprising a test machine 2 and a turbofan assembly 3 (also called turbofan assembly 3) being tested on the test machine 2.

[0006] In particular, the test machine 2 includes a fixed fairing 20, a first thrust measuring balance 22 and a second thrust measuring balance 24.

[0007] The turbofan assembly 3 includes a blower 32, also called a fan, a rotating part 31 about the X-axis, a turbofan shaft 31 and a fixed part 30 called fixed part 30 of turbofan in the suite.

[0008] The turbofan assembly 3 is mounted on the test machine 2.

[0009] In particular, the rotating blower 32 delivers an annular airflow having for axis of revolution the axis X, with a central annular part, called primary flow Fl, to supply air to parts of the engine such as a low pressure compressor - not shown on the [Fig.1] - and an outer annular part, called secondary flow F2, which is ejected providing a significant fraction of the thrust.

[0010] The fixed part 30 of the turbofan includes in particular a primary part 300, a secondary part 302, a nacelle 304 and an internal fixed structure 306 also called an IFS cowl (from the English "inner fixed structure").

[0011] The primary part 300 comprises a plurality of blades 301 also called primary flow fixed blade or IGV (“Inlet Guide Vane”) whose role is to straighten the primary flow Fl in the axis of the motor.

[0012] In addition, the primary part 300 comprises an internal primary housing 300i and an external primary housing 300e between which the plurality of blades included in the primary part 300 extend axially.

[0013] The secondary part 302 includes a plurality of vanes 303 called secondary fixed flow vanes or OGV (“Outlet Guide Vane”) whose role is to straighten the secondary flow F2 in the axis of the motor.

[0014] In particular, the fixed internal structure 306 extends axially, along the X axis, from the secondary part 302. The fixed internal structure 306 includes an external housing 306e which corresponds to a surface of revolution with axis X.

[0015] The secondary part 302 comprises an internal secondary housing 302i, extending from the external primary housing 300e, and an external secondary housing 302e between which the plurality of blades included in the secondary part 302 extend axially.

[0016] The primary inner casing 300i and the primary outer casing 300e together form a first part of a primary conduit 308 of the primary part 300. The primary inner casing 300i and the secondary inner casing 302i together form a second part of the annular primary flow conduit 308 extending from the first part. In particular, the primary flow conduit 308 forms a channel of the primary flow FL

[0017] In addition, the fixed part 30 of the turbofan includes a hub 310, visible in [Fig.2], the hub 310 comprising a cylindrical body 3100, having the axis of revolution X as its axis, and a plurality of hub arms 3102 shown schematically, (equi)distributed around the cylindrical body 3100.

[0018] Each hub arm 3102 extends radially from the cylindrical body to an external fixing ring 3104, visible in [Fig.2], fixed to the secondary internal housing 302i.

[0019] In particular, each hub arm 3102 includes a portion passing through the primary flow conduit 308.

[0020] With reference to the first balance 22, this one is rotating relative to the fixed fairing 2 and comprises a first part, not visible, mounted on the blower 32 and a second part, not visible, mounted on the turbofan shaft 31, so as to measure the forces applied to the blower.

[0021] The second balance 24 is fixed and includes a part fixed to the fixed fairing 20, and a measuring part fixed to the hub 310.

[0022] Thus, the plurality of arms of the hub allows the measuring part of the second balance 24 to be connected to the assembly formed by the nacelle 304, the primary part 300, the secondary part 302 and the fixed internal structure 306.

[0023] When the primary flow Fl passes through the primary conduit 308, the second balance 24 is intended to measure only the aerodynamic forces applied to the nacelle 304, the primary part 300, secondary part 302 and fixed internal structure 306.

[0024] However, it has become apparent that there are measurement errors by the fixed balance.

[0025] The invention remedies this situation. Summary of the invention

[0026] The presence of multiple hub arms interferes with the primary flow and alters the measurement of aerodynamic forces by the first balance. Thus, measurement errors appeared due to the presence of multiple hub arms interfering with the primary flow.

[0027] The invention makes it possible to answer this problem by isolating the aerodynamic forces applied to the plurality of hub arms from the forces applied to the nacelle, the primary part, the secondary part and the fixed internal structure.

[0028] The invention offers a solution to the problems mentioned above, by allowing the integration of an isolation deflector on each hub arm and the fixing of each isolation deflector on the fixed fairing not weighed by the balance, the isolation deflectors allowing the aerodynamic forces applied on the arms to be isolated and transmitted to the fixed fairing of a test machine.

[0029] One aspect of the invention relates to a fixed part of a turbofan adapted for testing on a test machine, comprising: • A primary part comprising a primary internal casing, • A secondary part comprising a secondary inner casing forming a primary flow conduit with the primary inner casing, the primary flow conduit defining a primary flow channel volume, • A hub comprising: • a cylindrical body to be fixed to a balance of the testing machine and; • a hub arm extending radially from the cylindrical body to an external mounting end fixed to the secondary internal casing, the hub arm comprising a portion passing through the primary flow conduit, • An isolation deflector for the hub arm located in the primary flow duct, movably interposed between the cylindrical body and the secondary internal casing, the isolation deflector comprising: • a fixing part including a trailing edge of the deflector, adapted to fix the deflector to a fixed fairing of the test machine.

[0030] By "turbofan" we mean a turbofan engine.

[0031] Thanks to the invention, the aerodynamic forces applied by the primary flow to the plurality of hub arms are transmitted to the fairing via the isolation deflectors and No, the fixed fairings are not connected to the measuring section of the thrust balance. Therefore, the balance only measures the aerodynamic forces applied to all elements of the turbofan's fixed section, with the exception of the hub arms.

[0032] In addition to the characteristics just mentioned in the preceding paragraph, the fixed part according to an aspect of the invention may have one or more complementary characteristics from among the following, considered individually or according to all technically possible combinations.

[0033] In one embodiment, the isolation deflector comprises an upstream part including a leading edge of the isolation deflector, an intrados wall and an extrados wall each extending from the upstream part to the fixing part, the intrados wall, the extrados wall the fixing part and the upstream part together defining an opening housing the through part of the hub arm.

[0034] In one embodiment, the deflector is formed of: • An intrados shell comprising the intrados wall, a first portion of the fixation part and a first portion of the upstream part, • An extrados shell assembled with the intrados shell forming the deflector, comprising the extrados wall, and a second portion of the fixing part and a second portion of the upstream part.

[0035] In one embodiment, the isolation deflector comprises: • a first assembly hole passing through the intrados and extrados shell at the level of the fixing part and a first assembly pin in the first assembly hole, fixing the intrados shell to the extrados shell, a second assembly hole passing through the intrados and extrados shell at the level of the upstream part and a second assembly pin inserted in the second assembly hole, fixing the intrados shell to the extrados shell.

[0036] In one embodiment, each isolation deflector includes a guide pin in the fixing part, to be inserted into a groove in the fixed fairing of the test machine.

[0037] In one embodiment, the fixed part according to the invention comprises a nacelle, and the secondary part comprises a secondary external casing fixed to the nacelle.

[0038] In one embodiment, the fixed part comprises a fixed internal structure extending from the secondary part.

[0039] Another aspect of the invention relates to a method, implemented by the fixed part of the turbomachine according to the invention, for mounting the isolation deflector on the hub arm, the method comprising: • Assembly of the lower surface shell and the upper surface shell around the hub arm, • Insertion of: • A first assembly pin in the first assembly hole included in the fixing part, • A second assembly pin in the second assembly hole included in the upstream part, to fix the intrados shell to the extrados shell.

[0040] Another aspect of the invention relates to an assembly comprising the fixed part of the turbofan according to the invention (with or without one or more of the different features described above), and the fixed fairing, the fixing part being fixed to the fixed fairing.

[0041] According to one example, the assembly further comprises the test machine, which also includes fixed fairing: • A thrust measurement balance for the forces applied to the fixed part of the turbofan, the thrust measurement balance being fixed to the fixed fairing and comprising a measuring part mounted on the hub of the fixed part of the turbofan and the fixed fairing. • Fastening means, inserted into the fixing hole of the isolation deflector to the fixed fairing.

[0042] In addition to the characteristics just mentioned in the preceding paragraph, the assembly according to one aspect of the invention may have one or more complementary characteristics from among the following, considered individually or according to all technically possible combinations.

[0043] In one embodiment, the fastening means include a screw.

[0044] In one embodiment, the fixed fairing comprises an outer casing and a casing internal forming together an extension of the primary flow channel.

[0045] In one embodiment, the isolation deflector is fixed to one end of the external housing of the fixed fairing.

[0046] In one embodiment, the turbofan assembly includes a blower and a turbofan shaft.

[0047] The invention and its various applications will be better understood by reading the following description and examining the accompanying figures. BRIEF DESCRIPTION OF THE FIGURES

[0048] Other advantages and features of the invention will become apparent from the following description, illustrated by the figures in which:

[0049] [Fig.1] is an axial cross-sectional view of an assembly comprising a test machine, a fixed part of a turbofan and a turbofan blower, according to the prior art;

[0050] [Fig.2] is a front view of the hub of the fixed part of the turbofan of [Fig.1];

[0051] [Fig.3] is an axial cross-sectional view of an assembly comprising a test machine, a fixed part of a turbofan and a turbofan blower, according to the invention;

[0052] [Fig.4] is a partial perspective view of part of the fixed fairing of the test machine, on which an isolation deflector is fixed, and of the hub comprising an arm surrounded by the deflector;

[0053] [Fig.5] represents the insertion according to a partial perspective view of the deflector in the fixed fairing of the test machine;

[0054] [Fig.6] is a perspective view of the hub including isolation deflectors on each of its arms;

[0055] [Fig.7] is a perspective view of the assembly of an extrados shell and an intrados shell around a hub arm;

[0056] [Fig.8] represents the attachment according to a perspective view of the extrados shell to the intrados shell to obtain a deflector for the arm. DETAILED DESCRIPTION

[0057] An example of an embodiment of an assembly comprising a test machine and a turbofan assembly including a fixed part according to the invention is described in detail below, with reference to the accompanying drawings. This example illustrates the features and advantages of the invention.

[0058] Unless otherwise specified, the same element appearing on different figures has a unique reference.

[0059] In the description, the terms "internal" and "external" are defined with respect to the X axis, for example the term "internal casing" designates the casing closest to the axis of rotation X, as opposed to the term "external casing" which designates the casing furthest from the X axis.

[0060] Fig. 3 represents an assembly 1' comprising a test machine 2' and a turbofan assembly 3' according to the invention.

[0061] The test machine 2' is identical to the test machine 2 shown in [Fig.1] of the prior art except that it also includes means for fixing, explained below, to the fixed fairing 20. Identically, it also includes a first thrust measuring balance 22 and a second thrust measuring balance 24.

[0062] The turbofan assembly 3' is identical to the turbofan assembly 3 of [Fig.1] except with regard to the fixed part 30 according to the invention, also called the fixed part 30 of the turbofan in the following.

[0063] The turbofan assembly 3' is mounted on the test machine 2'.

[0064] In particular, the rotating blower 32 delivers the primary flow Fl, to supply air to parts of the turbofan engine - not shown in [Fig. 3] - and the flow se- secondary F2, which is ejected providing a significant fraction of the thrust.

[0065] The first thrust measuring balance 22 and the second thrust measuring balance 24 are fixed on the test machine 2 and on various elements of the turbofan assembly 3 detailed in the following text.

[0066] The fixed part 30 of the turbofan, according to an example of a first aspect of the invention, includes in particular a primary part 300, a secondary part 302, a nacelle 304 and an internal fixed structure 306 also called an IFS hood (from the English "inner fixed structure").

[0067] The primary part 300 has the role of straightening the primary flow Fl in the axis of the motor. The primary part 300 comprises a plurality of vanes - also visible in [Fig.3] - also called fixed primary flow vanes or IGVs ("Inlet Guide Vane").

[0068] In addition, the primary part 300 comprises an internal primary housing 300i and an external primary housing 300e between which the plurality of blades included in the primary part 300 extend axially.

[0069] The secondary part 302 has the role of straightening the secondary flow F2 in the axis of the motor. The secondary part 302 comprises a plurality of vanes - only three are shown - also called fixed secondary flow vanes or OGVs ("Outlet Guide Vane").

[0070] In particular, the fixed internal structure 306 extends axially, along the X axis, from the secondary 302. The fixed internal structure 306 includes an external housing 306e which corresponds to a surface of revolution with axis X.

[0071] The secondary part 302 comprises an internal secondary housing 302i, which is indistinguishable from the external primary housing 300e, and an external secondary housing 302e between which the plurality of blades included in the secondary part 302 extend axially.

[0072] In particular, the nacelle 304 is mounted on the secondary external casing 302e.

[0073] The primary inner casing 300i and the secondary inner casing 302i together form an annular primary flow conduit 308. In particular, the primary flow conduit 308 forms a primary flow channel FL

[0074] In this example, the primary internal casing 300i comprises on the one hand a first upstream part in the shape of a crown from which extend the blades of the primary part 300 forming with the primary external casing 300e the rectifier conduit and on the other hand a second downstream part in the shape of a crown mounted coaxially against the first part, the second part being surrounded by the secondary internal casing 302i forming together the conduit 308 following the rectifier conduit.

[0075] In addition, the fixed part 30 of the turbofan includes a hub 310, which is fully or partially visible in [Fig.4], [Fig.5], [Fig.6], [Fig.7] and [Fig.8].

[0076] The hub 310 comprises a cylindrical body 3100, having as its axis of revolution the X axis, and a plurality of hub arms 3102 equally distributed around the cylindrical body 3100.

[0077] Each hub arm 3102 extends radially from the cylindrical body 3100 to an external fixing ring 3104, visible on [Fig.5] and on [Fig.6], fixed to the secondary inner housing 302i.

[0078] In particular, each hub arm 3102 includes a portion passing through the primary flow conduit 308.

[0079] In a preferred embodiment, the through part of each hub arm hub arm 3102 is a block.

[0080] The fixed part 30 of the turbofan, according to a first aspect of the invention, further comprises a plurality of isolation deflectors 312 – only one of which is shown in [Fig. 3] – each isolation deflector 310 being placed on a hub arm 3102, so as to surround said hub arm 3102. In other words, an isolation deflector 312 is placed on each hub arm 3102. More particularly, when the fixed part 30 is not fixed to the fixed fairing 20 of the test machine 2', each deflector 3102 is interposed between the cylindrical body 3102 of the hub and the secondary internal casing 302i, so as to be movable by surrounding the arm. Thus, each deflector separates a portion of the primary flow channel into two paths (one path on the lower surface and the other path on the upper surface). Each path of the primary flow channel is therefore formed between two deflectors.

[0081] In particular, each isolation deflector 312 comprises a leading edge 312A and a trailing edge 312F, visible in [Fig. 4], [Fig. 5], [Fig. 6], [Fig. 7], and [Fig. 8], so as to deflect a portion of the primary flow Fl so that aerodynamic forces due to that portion of the primary flow Fl are not applied to the hub arm 3102 on which the isolation deflector 312 is mounted. Indeed, each isolation deflector 312 separates a portion of the primary flow channel Fl that it receives into two distinct paths.

[0082] As a result, the test machine 2 makes it possible to verify the ability of the blower 32 to achieve the counter-thrust without measurement errors related to the force exerted by the airflow on the hub arms and thus to verify the proper supply of the primary flow in this operating mode.

[0083] In particular, as seen in [Fig.4], [Fig.5], [Fig.7] and [Fig.8], the isolation deflector 312 includes a fixing part 3120 comprising the trailing edge 312F of the isolation deflector 312, an intrados wall 312i, an extrados wall 312e and an upstream part 3122 comprising the leading edge 312A.

[0084] The intrados wall 312i and the extrados wall 312e each extend from the attachment part 3120 to the upstream part 3122. In particular, the intrados wall 312i and the extrados wall 312e together define an opening that accommodates the through part of the hub arm 3102.

[0085] Thus, each deflector 312 has an aerodynamic profile to deflect the primary flow Fl.

[0086] In one embodiment, each isolation deflector 312 is symmetrical and the intrados wall 312i and the extrados wall 312e thus have the same curvature.

[0087] A second aspect of the invention relates to an assembly comprising a turbofan test machine and a turbofan assembly including the fixed part of the turbofan. Each isolation deflector 312 is fixed to the fixed fairing 20. Each isolation deflector 312 thus includes a fixing hole 3124 included in the fixing part 3120, into which a fixing screw 200 is inserted, passing through a fixing hole in the fixed fairing 20. Thus, each isolation deflector 312 is fixed to the fixed fairing 20 by means of the fixing hole 3124 and the fixing screw 200.

[0088] In particular, the fixed fairing 20 comprises an inner casing 20i and an outer casing 20e jointly forming an extension 201 of the primary flow duct 308, each isolation deflector 312 being included both in the primary flow duct 308 and in the extension 201 of the duct 308 and being fixed in the extension 201 of the duct 308.

[0089] In a preferred embodiment, each isolation deflector 312 is fixed to the outer casing 20e of the fixed fairing 20. More particularly, each isolation deflector 312 is fixed to one end of the outer casing 20e of the fixed fairing 20.

[0090] In particular, the end to which each isolation deflector 312 is attached includes a fixing hole 202 for receiving the screw 200 for fixing the isolation deflector 312 to the external housing 20e of the fixed fairing 20.

[0091] In another embodiment, each isolation deflector 312 is fixed to the inner casing 20i of the fixed fairing 20. More particularly, each isolation deflector 310 is fixed to one end of the inner casing 20e of the fixed fairing 20. In particular, the end to which each isolation deflector 312 is fixed corresponds to the end extending from the primary flow duct 308.

[0092] With reference to the first balance 22, this one is rotating relative to the fixed fairing 2 and comprises a first part, not visible, mounted on the blower 32 and a second part, not visible, mounted on the turbofan shaft 31, so as to measure the forces applied to the blower.

[0093] The second balance 24 is fixed and includes a part fixed to the fixed fairing 20, and a measuring part fixed to the hub 310.

[0094] Thus, the plurality arm 3102 of the hub 310 allows the measuring part of the second balance 24 to be connected to the assembly formed by the nacelle 304, the primary part 300, the secondary part 302 and the fixed internal structure 306.

[0095] When the primary flow Fl passes through the primary conduit 308, the second balance 24 is intended to measure only the aerodynamic forces applied to the nacelle 304, the primary part 300, the secondary part 302 and the fixed internal structure 306. The arrangement of the plurality of isolation deflectors 312 on the plurality of arms 3102 of the hub and their attachment to the fixed fairing 20 - not measured by the balance - and not at the level of the hub 310 advantageously avoids the measurement of the aerodynamic forces applied to the plurality of arms of the hub 3102.

[0096] Fig. 4 is a partial perspective view of a portion of the primary part 300, a portion of the fixed fairing 20, a portion of the cylindrical body 3100 of the hub and a hub arm 3102 and an isolation deflector 312 deposited on the hub arm 3102.

[0097] In particular, each isolation deflector 312 is formed of an intrados shell 3126 and an extrados shell 3128 assembled, visible in [Fig.7] and [Fig.8].

[0098] In particular, each isolation deflector 312 includes a first assembly hole 3130 and a first assembly pin 3131, visible in [Fig.7], included in the fixing part 3120. The first assembly pin 3131 is inserted into the first assembly hole 3130.

[0099] In addition, each isolation deflector 312 includes a second assembly hole 3132 and a second assembly pin 3133, visible in [Fig.7], included in the upstream portion 3122. The second assembly pin 3133 is inserted into the second assembly hole 3132.

[0100] The first 3131 and second 3133 assembly pins deform elastically (but could also deform plastically) in the assembly holes so as to be mounted tightly in the holes.

[0101] Thus, the first 3130 and second 3132 assembly holes and the first 3131 and second 3133 assembly pins allow the intrados shell 3126 and the extrados shell 3128 to be assembled.

[0102] The intrados shell 3126 includes a first portion of the fixing part 3120, the intrados wall 312i, and a first portion of the upstream part 3122. In addition, the intrados shell 3126 includes a first portion 41 of the fixing hole 3124, the first portion 41 being tapped.

[0103] The extrados shell 3128 includes a second portion of the fixing part 3120, the extrados wall 312e, and a second portion of the upstream part 3122. In addition, the extrados shell 3128 includes a second portion 43 of the fixing hole 3124.

[0104] In particular, the extrados shell 3128 is located between the external casing 20e of the fixed fairing 20 and between the intrados shell 3126.

[0105] Figure 5 shows, in a partial perspective view, the insertion of an isolation deflector 312 under the end of the outer casing 20e of the fixed fairing 20 intended to receive the isolation deflector 312. In particular, the end of the outer casing 20e includes an imprint 203 of the fixing part 3120. In the embodiment of [Fig.5], the isolation deflector 312 includes a guide pin 3012 for being inserted into a groove 204 located at the end of the outer casing 20e of the fixed fairing 20.

[0106] Advantageously, the guide pin 3012 inserted in the groove 204 allows the insulation deflector 312 to be guided so as to make the fixing hole 202 of the outer casing 20e coincide with the fixing hole 3122 of the insulation deflector 312 in order to facilitate the insertion of the screw 200. In other words, with the insulation deflector 312 being movable on the hub arm 3102, it is possible to have some play between the insulation deflector 312 and the hub arm 3102.

[0107] Thus, the insertion of the guide pin 3012 into the groove 204 makes it possible to eliminate this play of the isolation deflector 312 with respect to the external housing 20e.

[0108] Fig. 6 represents the hub 310, the outer fixing ring 3104 and the plurality of deflectors 312 surrounding the plurality of hub arms 3102, not visible in this figure.

[0109] Another aspect of the invention relates to a method of mounting an isolation deflector 312 on a hub arm 3102.

[0110] The method includes a step of assembling the intrados shell 3126 and the intrados shell 3128 around the hub arm 3102, the step being visible in [Fig.7].

[0111] The process includes an insertion step, visible in [Fig. 8], of: • the first assembly pin 3131 in the first assembly hole 3130 included in the fastening part 3120, • the second assembly pin 3133 in the second assembly hole 3132 included in the upstream part 3122, the deflector being movably interposed around the arm between the cylindrical body 3100 and the secondary internal housing 302i

[0112] Another aspect of the invention relates to a method of mounting the deflector of the fixed part to the fairing, comprising a step of adjusting the fixing hole 3124 with the fixing hole of the fixed fairing 20 and a step of inserting a screw through the fixing hole of the fixed fairing 20, of the second portion 43 of the fixing hole 3120 passing through the extrados wall 312e and a step of screwing the screw into the tapping of the first portion 41 of the fixing hole 3124 passing through the intrados hull 3126.

Claims

Demands

1. A fixed part (30) of a turbofan adapted for testing on a test machine, comprising: - A primary part (300) including a primary inner casing (300i), - A secondary part (302) including a secondary inner casing (302i) forming a primary flow duct (308) with the primary inner casing (300i), the primary flow duct (308) defining a primary flow channel volume, - A hub (310) including: • a cylindrical body (3100) for being fixed to a thrust measuring balance of the test machine and;• a hub arm (3102) extending radially from the cylindrical body (3100) to an external mounting end (3124) fixed to the secondary inner housing (302i), the hub arm (3102) comprising a portion passing through the primary flow conduit (308), - An isolation deflector (312) of the hub arm (3102) located in the primary flow conduit (308), movably interposed between the cylindrical body (3100) and the secondary inner housing (302i), the isolation deflector (312) comprising: • a mounting portion (3120) comprising a trailing edge (312F) of the deflector (312), adapted to fix the deflector (312) to a fixed fairing (20) of the test machine (2').;

2. Fixed part (30) according to the preceding claim in which the isolation deflector (312) comprises an upstream part (3122) including a leading edge (312A) of the isolation deflector (312), an intrados wall (312i) and an extrados wall (312e) each extending from the upstream part (3122) to the fixing part (3120), the intrados wall (312i), the extrados wall (312e) the fixing part (3120) and the upstream part (3122) together defining an opening housing the through portion of the hub arm (3102).

3. Fixed part (30) according to the preceding claim in which the deflector is formed of: - An intrados shell (3126) comprising the intrados wall (312i), a first portion of the fixing part (3120) and a first portion of the upstream part (3122), - An extrados shell (3128) assembled with the intrados shell (3122) forming the deflector (312), comprising the extrados wall (312e), a second portion of the fixing part (3120) and a second portion of the upstream part (3122).

4. Fixed part (30) according to the preceding claim in which the isolation deflector (312) comprises: - a first assembly hole (3130) passing through the lower surface shell (3126) and upper surface shell (3128) at the level of the fixing part (3120) and a first assembly pin (3131) in the first assembly hole (3130), fixing the lower surface shell (3126) to the upper surface shell (3128), - a second assembly hole (3132) passing through the lower surface shell (3126) and upper surface shell (3128) at the level of the upstream part (3122) and a second assembly pin (3133) inserted in the second assembly hole (3132), fixing the lower surface shell (3126) to the upper surface shell (3128).

5. Fixed part (30) according to any one of the preceding claims wherein the isolation deflector (312) comprises a guide pin (3012) in the fixing part (3120) for being inserted into a groove (204) of the fixed fairing (20) of the test machine (2).

6. Fixed part (30) according to any one of the preceding claims comprising a nacelle (304), and wherein the secondary part (302) comprises a secondary external casing (302e) fixed to the nacelle (304).

7. Fixed part (30) according to any one of the preceding claims comprising a fixed internal structure (306) extending from the secondary part (302).

8. Assembly comprising the fixed part (30) according to any one of claims 1 to 7, and the fixed fairing (20), the fixing part (3120) being fixed to the fixed fairing (20).

9. Assembly according to claim 8, comprising a turbofan testing machine (2') further comprising a fixed fairing (20): - A thrust measuring balance (24) for the forces applied to the fixed part (30) of the turbofan, the thrust measuring balance (24) being fixed to the fixed fairing (20) and comprising a measuring portion mounted on the hub (310) of the fixed part (30) of the turbofan and the fixed fairing (20). - Fastening means, inserted into the mounting hole of the isolation deflector, securing the isolation deflector (312) to the fixed fairing (20).

10. Assembly according to any one of claims 9 to 10 wherein the fixed fairing (20) comprises an outer casing (20e) and an inner casing (20i) together forming an extension of the primary flow channel.

11. Assembly according to the preceding claim in which the outer casing includes a fixing hole through which the fixing means attaches the isolation deflector (312) to the outer casing of the fixed fairing.

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