FR3093539A1 - Device for maintaining the cooling tube by air jet, turbomachine for aircraft having it - Google Patents

Abstract

The invention relates to a device (100) for holding a tube (T) for cooling by air jet, having a base (101) on the outer surface (190) of the housing (19), a connecting piece (150) retained in the element (101), a support (130) for the tube (T) comprising a cross member (131) having an opening (132) traversed by the part (150), a spacer (120) surrounding the part (150) so that the spacer (120) bears against the cross member (131) and the projecting part (102), a retaining means (140), fixed to the part (150), a return element (170) between the retaining means (140) and the cross member (131), biased in compression towards the cross member (131). Figure for abstract: 4

Description

Device for holding a cooling tube by air jet, turbomachine for an aircraft having the same

The invention relates to a device for holding at least one cooling tube by air jet, as well as a turbomachine equipped with this device.

One field of application concerns aircraft turbojets.

The casing may be that of a low pressure turbine of the turbomachine. Cooling tube is also called cooling ramp. Usually several cooling tubes are provided. The cooling device is fixed radially at a distance so as to define an air gap with respect to the external surface of the casing. This air gap allows the cooling tubes in particular to cool the crankcase by air jet.

Different holding devices of this type are known.

According to a state of the art, the cooling tubes are secured by means of supply boxes with the external surface of the casing that they must cool. It is also necessary to ensure proper positioning of the cooling tubes acting on the casing, in particular at the places farthest from the power supply units; to this end, provision is made in the state of the art for the use of a fixing plate which comprises a flat plate under which collars are fixed, said collars surrounding the cooling tubes, allowing said tubes to be held in position relative to the housing.

FIG. 1a shows a first perspective view of a cooling device 1 for a turbojet engine casing according to the state of the art. Figure 1a shows as follows:

- A turbojet casing 2;

- the cooling device 1 for said casing 2 of the turbojet engine, the cooling device 1 comprising a plurality of cooling tubes 3, a box 4 for supplying air to the plurality of cooling tubes 3, a plurality of fixing plates 5 for holding the plurality of cooling tubes 3 in position.

FIG. 1b shows a second perspective view of the cooling device 1 for the casing 2 of a turbojet engine according to the state of the art. Figure 1b shows in particular a fixing plate 5 under which is fixed a plurality of collars 6, each collar 6 surrounding a cooling tube 3.

Such a solution does not make it possible to systematically ensure correct positioning of the cooling device 1 relative to the casing 2. There are thus found incorrect positionings of the cooling tubes 3 of the cooling device relative to the casing 2, due to tolerances of the parts of the device, due for example to the presence of stamped sheets. These incorrect positions are typically axial and/or radial misalignments of the cooling tubes 3 of the cooling device with respect to the casing 2.

FIG. 2a schematically illustrates an example of correct positioning of a cooling tube 3 of the cooling device 1 for the casing 2 of the turbojet engine, with respect to the casing 2 of the turbojet engine.

In the example in Figure 2a:

- the axial positioning, in an axial direction Ax, of the cooling tube 3 is correct, the cooling tube 3 being aligned with a hook 7 of the casing 2, and

- The radial positioning, in a radial direction Rad, of the cooling tube 3 is correct, the radial distance between the cooling tube 3 and the casing 2 being controlled.

Figure 2b schematically illustrates a first example of incorrect positioning of the cooling tube 3 relative to the casing 2 of the turbojet engine, in which the collar of the cooling tube 3 is in contact with said casing 2.

FIG. 2c schematically illustrates a second example of incorrect positioning of the cooling tube 3 with respect to the casing 2 of the turbojet engine, in which said cooling tube 3 is this time away from said casing 2 (radial misalignment) in order to have effective cooling of the casing. The sum of the tolerances, taking into account the intermediate parts, can impose a large air gap according to figure 2c in order to avoid contact between the collar and the housing according to figure 2b.

Finally, FIG. 2d schematically illustrates a third example of incorrect positioning of the cooling tube 3 with respect to the casing 2 of the turbojet engine, in which said cooling tube 3 is misaligned with respect to a hook 7 of said casing 2 along the axial direction Ax (axial misalignment).

Document FR-A-2 995 022 relates to a fixing device comprising a fixing plate comprising recesses on which are also fixed fixing collars surrounding the cooling tubes, the fixing plate being fixed by its first and second ends to two housing flanges.

The document FR-A-3 021 700 relates to a fixing device comprising two plates fixed together by spacers defining between them spaces in which the cooling tubes pass, one of the plates being arranged in integral contact with the casing of turbojet. Such a solution makes it possible to minimize the accumulation of tolerances and to better control the positioning of the cooling tubes.

However, this device is sensitive to situations where strong stresses are exerted on the outer surface of the casing in operation, for example as a result of vibratory phenomena or expansions exerted on the casing.

The aim of the invention is to obtain a holding device which makes it possible to reduce the air gap between the external surface of the casing and the cooling tube by avoiding incorrect positioning of the tube due to the tolerances of the parts holding the tube and which lends itself to variations dimensions of the outer surface of the casing in operation, in particular due to thermal expansion of the latter.

To this end, a first object of the invention is a device for holding at least one air jet cooling tube extending around an axis, the air jet cooling tube being intended to cooling an external surface of a turbomachine casing,

characterized in that the device comprises:

a base intended to be fixed on the outer surface of the casing,

a connecting part comprising an outer end part, an inner end part, which is retained in a projecting part of the base, and an intermediate part, which is located between the outer end part and the inner end,

a support to which the at least one cooling tube is intended to be fixed, the support comprising a crosspiece having a passage opening through which the intermediate part of the connecting piece passes,

a spacer which extends in a longitudinal direction and which surrounds the intermediate part of the connecting piece, the spacer having, in a section plane transverse to the longitudinal direction, a width greater than a dimension of the opening so that the spacer bears on the one hand against the crosspiece and on the other hand against the projecting part,

a retaining means, fixed to the outer end part of the connecting piece,

a return element, which extends between the retaining means and the crosspiece and which is biased in compression towards the crosspiece.

Thanks to the invention, the holding device absorbs by its elastic return element the radial expansions of the outer surface of the casing to maintain a minimum and constant air gap between this outer surface and the cooling tube, guaranteeing correct positioning of the tube. cooling which does not depend on the tolerances of the constituent parts of the holding device and avoiding damage due to these expansions, contrary to document FR-A-3 021 700.

According to one embodiment of the invention, the passage opening has in the section plane a section greater than the section of the intermediate part, so as to allow movement between the connecting piece and the crosspiece.

According to one embodiment of the invention, the passage opening has an oblong shape having a length along a circumferential direction of the outer surface of the casing, which is greater than the dimension of the passage opening extending along the axis, around which extends the outer surface of the housing.

According to one embodiment of the invention, the passage opening has an oblong shape having a length along a circumferential direction of the outer surface of the casing, which is at least equal to 1.5 times the dimension of the passage opening s extending along the axis around which extends the outer surface of the housing.

According to one embodiment of the invention, the retaining means comprises a sleeve, which is retained at the outer end part of the connecting piece and which comprises at its radially outer end an end part serving as an abutment for the return element, the return element being biased in compression between the end part of the sleeve and the crosspiece.

According to one embodiment of the invention, the retaining means comprises a widened section which is fixed to the outer end part of the connecting piece, the sleeve is arranged to act as an abutment against the widened section.

According to one embodiment of the invention, the connecting piece is a screw, having a head forming the internal end part and a thread at least on the external end part,

the retaining means being formed by a nut screwed onto the thread.

According to one embodiment of the invention, a washer for supporting the return element is arranged against an outer face of the crosspiece and around the intermediate part of the connecting piece.

According to one embodiment of the invention, the internal end part has a widened section with respect to the intermediate part,

the projecting part of the base comprises at least two hooking lugs, which are spaced apart from each other by a gap used for the passage of the intermediate part and against which the widened section of the part of the inner end.

According to one embodiment of the invention, each hooking lug comprises an internal abutment surface against the widened section of the internal end part and an external abutment surface against the spacer.

According to one embodiment of the invention, the internal abutment surface and the external abutment surface extend circumferentially around the axis.

According to one embodiment of the invention, the outer surface of the casing has a determined inclination with respect to the axis around which the outer surface extends,

the retaining element comprises an internal part for fixing to the external surface, the hooking tabs having the reverse determined inclination with respect to the internal fixing part so that the hooking tabs are parallel to the axis.

According to one embodiment of the invention, the internal abutment surface and the external abutment surface have the opposite determined inclination with respect to the internal fixing part so that the internal abutment surface and the external abutment surface are parallel to the axis.

According to one embodiment of the invention, each hooking lug is extended by a respective front edge, the lugs defining between them a space used for the introduction of the intermediate part along the axis.

According to one embodiment of the invention, the support comprises a first sheet and a second sheet, which are fixed on either side of the crosspiece and which extend axially, a plurality of cooling tubes being fixed to the following axially one behind the other to the first sheet and to the second sheet.

According to one embodiment of the invention, the determined direction is radial towards the axis around which the outer surface extends.

A second object of the invention is a turbine engine for an aircraft, comprising a casing having an annular external surface, at least one cooling tube by air jet, which is intended to cool the external surface of the casing, at least one retaining as described above, attached to the outer surface of the housing to maintain the at least one cooling tube outside the outer surface of the housing.

According to one embodiment of the invention, the turbomachine comprises a first number, greater than or equal to two, of holding devices, the supports of which comprise the same first sheet and the same second sheet, which are fixed on either side other of their crosspieces and which extend in the axial direction,

a second number of cooling tubes, greater than the first number, being fixed one behind the other to the first sheet and to the second sheet.

According to one embodiment of the invention, each connecting piece and each spacer are located between two of the cooling tubes.

The invention will be better understood on reading the following description, given solely by way of non-limiting example with reference to the figures of the appended drawings, in which:

schematically represents a perspective view of an example of a holding device according to a state of the art,

schematically represents a perspective view of the holding device according to FIG. 1a according to the state of the art,

schematically represents a view in axial section of a cooling tube in a correct position with respect to the casing according to figure 1a according to the state of the art,

schematically represents a view in axial section of a cooling tube in an incorrect positioning with respect to the casing according to figure 1a according to the state of the art,

schematically represents a view in axial section of a cooling tube in an incorrect positioning with respect to the casing according to figure 1a according to the state of the art,

schematically represents a view in axial section of a cooling tube in an incorrect positioning with respect to the casing according to figure 1a according to the state of the art,

schematically shows in axial section an example of a turbomachine on which the holding device and the mounting method according to the invention can be used,

schematically represents a top perspective view of a holding device according to one embodiment of the invention,

schematically represents a perspective view from below of a holding device according to one embodiment of the invention,

schematically represents a top perspective view of a holding device according to one embodiment of the invention,

schematically represents a front view of a holding device according to one embodiment of the invention,

schematically represents a front sectional view along a transverse plane of a holding device according to one embodiment of the invention,

schematically represents a view in section along an axial plane of a holding device according to one embodiment of the invention.

Described below in more detail with reference to Figure 3 an example of a turbine engine 10 on which can be used the device 100 for holding at least one cooling tube T outside an outer surface 190 of a casing of this turbomachine 10 according to the invention.

As is known, the turbine engine 10 represented in FIG. 1 is intended to be installed on an aircraft, not represented, in order to propel it in the air.

The gas turbine engine or turbomachine assembly 10 extends around an axis AX. Thereafter, the terms "upstream", respectively "downstream" or "front", respectively "rear", or "left" respectively "right" are taken along the general direction of the gases which flow in the turbomachine according to the axis AX or axial direction AX. The direction going from inside to outside is the radial direction DR starting from the axis AX. The term axially designates a direction along the axis AX. An axial plane is a plane containing the axis AX. A direction located in a plane transverse to the AX axis is called the transverse direction.

The turbomachine 10 is for example a double body. The turbine engine 10 includes a fan assembly 28 and a central gas turbine engine 130. The central gas turbine engine 130 includes, from upstream to downstream in the direction of gas flow, a low pressure compressor CBP1, a high pressure compressor CHP1, a combustion chamber 160, a high pressure turbine THP1 and a low pressure turbine TBP1, which delimit a primary flow of gas FP1. The fan assembly 28 includes a set of fan blades extending radially outward from a rotor 250. The turbomachine 10 has an upstream intake end 29 and a downstream exhaust end 31. The turbomachine 10 includes also an inter-stream casing 36 which delimits a primary stream in which circulates the primary flow FP1 which passes through the high pressure compressor CHP1, the high pressure turbine THP1 and the low pressure turbine TBP1.

The inter-vein casing 36 comprises, from upstream to downstream, a casing 361 of the low pressure compressor CBP1, an intermediate casing 260, which is interposed between the low pressure compressor CBP1 and the high pressure compressor CHP1, a casing 362 of the high pressure compressor CHP1, a casing 363 of the high pressure turbine THP1 and a casing 19 of the low pressure turbine TBP1.

The high pressure turbine THP1 is integral in rotation with the high pressure compressor CHP1 via a common rotation shaft (high pressure shaft) so as to form a high pressure body, while the low pressure turbine TBP1 is integral in rotation with the low pressure compressor CBP1 via a common rotation shaft (low pressure shaft) so as to form a low pressure body, so that each turbine drives the associated compressor in rotation around the axis AX under the effect of the thrust of the gases coming from the chamber combustion 160.

In operation, the air flows through the fan assembly 28 and a first part FP1 (primary flow FP1) of the airflow is routed through the high pressure compressor CHP1, in which the airflow is compressed and sent to the combustion chamber 160. The hot combustion products (not shown in the figures) coming from the combustion chamber 160 are used to drive the turbines THP1 and TBP1 and thus produce the thrust of the turbomachine 10. The turbomachine 10 also includes a secondary duct 39 which is used to pass a secondary flow FS1 of the airflow evacuated from the fan assembly 28 around the inter-vein casing 36. More specifically, the secondary duct 39 extends between a internal wall 201 of a fairing 30 of fan or nacelle 30 and the inter-vein casing 36 surrounding the central gas turbine engine 130. Arms 34 connect the intermediate casing 260 to the internal wall 201 of the fairing 30 in the second vein. dary 39 of the secondary stream FS1.

With reference to FIGS. 3 to 9, the holding device 100 according to the invention makes it possible to hold one or more cooling tubes T or one or more cooling ramps R, at an air gap, namely at a certain distance radially above of the external surface 190 of the casing and comprises means of attachment to this casing, this casing belonging to the inter-vein casing 36, this casing being in particular the casing 19 of the low pressure turbine TBP1 in the embodiments described below and which can alternatively be one of the casing 361 of the low pressure compressor CBP1, the intermediate casing 260, the casing 362 of the high pressure compressor CHP1, the casing 363 of the high pressure turbine THP1 and the casing 19 of the low pressure turbine TBP1 .

The crankcase is cooled using impact cooling technology. Each cooling tube T and/or each cooling ramp R is an air jet. To this end, each cooling tube T is pierced with a series of orifices, which are distributed along its length and which open out in line with the outer surface 190 of the casing 19. Each cooling ramp R can be formed of a or several interconnected cooling tubes T extending in the same transverse plane. Each cooling tube T has in a radial plane which includes the axis AX a curved outer surface TS, for example rounded or circular. Each cooling tube T can be metallic, for example steel. Each cooling tube T is curved and extends transversely over a certain angular range around the casing 19, for example over approximately 90°, namely around the axis AX. An air sending device DE is provided to send pressurized air into the cooling tube(s) T and thus project the jets of pressurized air through their orifices against the external surface 190 of the casing 19. Pressurized air passing through these orifices provides ventilation by impact of the casing 19. For example, several cooling tubes T arranged axially side by side are provided. For example, several angular ranges are provided, which go around the casing 19 and in each of which there are one or more cooling tubes T arranged axially side by side, for example four angular ranges of approximately 90° each. In the embodiment shown in Figures 3 to 9, the outer surface 190 of the housing 19 extends around the axial direction AX or axis AX. The outer surface 190 of the casing 19 is for example annular around the axis AX. For example, the casing 19 of the low pressure turbine TBP1 is of general shape having an outer surface 190 widening from upstream to downstream, for example substantially tapered, and the cooling tubes T are arranged in transverse planes side by side axially, having relative to the axis AX of the housing 19 a radial distance increasing from upstream to downstream to follow the outer surface 190.

The radial clearances of the low pressure turbine TBP1 between its rotor (the blade tips, not shown) and the casing 19 (the sealing sectors, not shown) surrounding this rotor are managed by cooling the casing 19 on which the sectors are fixed. sealing at the casing hooks, the sealing sectors being configured to cooperate with the rotor of the low pressure turbine TBP1. This system for cooling the casing of the low pressure turbine TBP1 can be of the LPTCC type (in English: Low Pressure Turbine Clearance Control) or else of the LPTACC type (in English: Low Pressure Turbine Active Clearance Control).

Air is taken from the secondary flow FS1 at the level of the low pressure compressor CBP1, then is routed to the cooling ramps R and/or to the cooling tube(s) T via the various elements described below. below the air delivery device DE.

In the case of an LPTCC-type cooling system, the flow in the system is directly proportional to the flow in the secondary flow (the sampling flow).

In an LPTACC type cooling system, the flow is controlled via a motorized valve connected to the computer according to the flight phases (takeoff, ascent, cruise, etc.).

For example, in the case of the LPTACC type cooling system, the air delivery device DE comprises:

- a valve, which is positioned upstream of the low pressure turbine TBP1 and which calibrates the flow required to control the clearances of the low pressure turbine TBP1 via a computer according to the flight phases,

- a pipe, which carries the cooling air from the valve to the low pressure turbine TBP1, and more particularly to boxes B,

- one or more pressurized air supply boxes B, each connected to one or more cooling ramps R located on either side of each of the boxes B and fixed to it. The boxes B act as a collector and distribute the air obtained in the ramps R.

- one or more cooling ramps R, each comprising one or more cooling tubes T and pierced on their part facing the casing 19, which project the cooling air onto the outer surface 190 of the casing 19, in order to reduce its temperature, consequently its diameter and therefore the overall diameter of the stator vis-à-vis the rotor.

In an exemplary embodiment, the casing 19 is equipped with two boxes B, positioned at approximately 180° from each other (only one being visible in FIG. 1a). Each box B is equipped with several ramps R. Each ramp R comprises for example two cooling tubes T fixed on either side of the box B.

The holding device 100 according to the invention is described below in more detail with reference to FIGS. 4 to 9.

The holding device 100 is provided to hold one or more cooling tubes T by jet of air intended to cool an external surface 190 of a casing 19 of the turbomachine.

The holding device 100 comprises a first base 101 or internal retaining element 101, intended to be fixed on the external surface 190 of the casing 19, and a connecting part 150 comprising an internal end part 152, which is retained in a projecting part 102 of the retaining base 101. The connecting part 150 comprises an intermediate part 153, which is located between an outer end part 151 and the inner end part 152, and is for example oblong in shape from its inner end part 152 to its outer part. external end 151. The retaining base 101 can be fixed by any appropriate means on the outer surface 190 of the casing 19, for example by one or more bolts 106.

The holding device 100 comprises a support 130 to which one or more cooling tube(s) T is intended to be fixed. The support 130 comprises a crosspiece 131 (or platform 131) having an opening 132 for passage. The connecting piece 150 passes through the passage opening 132 via its intermediate part 153.

The holding device 100 comprises a spacer 120, which is located between the crosspiece 131 and the projecting part 102. The spacer 120 extends in a longitudinal direction, going from the base 101 towards the crosspiece 131 and can for example be parallel to the radial direction DR. The crosspiece 131 presses by its radially inner surface 134 on the spacer 120. The spacer 120 presses on the projecting part 102 of the retaining base 101. The spacer 120 surrounds the intermediate part 153 of the connecting part 150 between the crosspiece 131 and the projecting part 102. The spacer 120 comprises, in a section plane transverse to the longitudinal direction, a width greater than a dimension of l opening 132 (for example in the axial direction AX as shown in Figure 9) so that the spacer 120 bears on the one hand against the crosspiece 131 and on the other hand against the projecting part 102.

The holding device 100 comprises a retaining means 140, or outer retaining assembly 140, fixed to the outer end portion 151 of the connecting part 150 and arranged to retain the crosspiece 131 on the connecting part 150.

The holding device 100 comprises a return element 170, which extends between the retaining means 140 and the crosspiece 131. This return element 170 may for example be elastic. The return element 170 is stressed in compression towards the crosspiece 131 by the connecting piece 150. The crosspiece 131 is thus pushed against the spacer 120 by the return element 170. The return element 170 is arranged radially on the outside of the crosspiece 131. The return element 170 is biased in compression towards the crosspiece 131 in a determined direction, which is for example the radial direction DR2 oriented from the outside. inwards, that is to say towards the axial direction AX.

The spacer 120 thus makes it possible to control and maintain substantially constant the air gap between the cooling tube or tubes T and the outer surface 190 of the casing 19, while absorbing by the return element 170 the radial expansions of the casing 19 to control the air gap, compared to document FR-A-3 021 700. The air gap is determined mainly by the height of the spacer 120 and the height of the crosspiece 131 above the outer surface 190. the air gap so that there is no contact between the support 130 serving to retain the cooling tube(s) T and the casing 19, and constant radial clearances are guaranteed in the low pressure turbine. In addition, controlling and reducing the air gap makes it possible to reduce the diameter of the cooling T tube(s), which saves weight, reduces air intake and therefore increases engine performance. By the fact that it adapts to the radial expansions of the casing 19, the holding device according to the invention prevents the system from being damaged by the formation of cracks.

According to one embodiment of the invention, the passage opening 132 has a section greater than the section of the intermediate part 153, so as to allow movement between the connecting piece 150 and the crosspiece 131, and therefore relative to the retaining base 101 and to the housing 19, for example to adapt to expansions. For example, as shown in Figures 5, 7, 8 and 9, the passage opening 132 has an oblong shape having a length along a circumferential or transverse direction DT of the outer surface 190 of the housing 19, which is greater than the dimension of the passage opening 132 in the axial direction AX, thus allowing movement of the crosspiece 131 in the transverse direction DT with respect to the connecting part 150 and therefore with respect to the retaining base 101 and to the casing 19. For example, the length of the passage opening 132 in the transverse direction DT is greater than or equal to 1.5 times the dimension of the passage opening 132 extending in the axial direction AX.

According to one embodiment of the invention, the retaining means 140 comprises a sleeve 145 retained at the outer end portion 151 of the connecting part 150. The sleeve 145 has at its radially outer end an end part 147, such as for example a collar 147, serving as a stop for the return element 170 in the centrifugal radial direction DR. The return element 170 is stressed in compression between the end part 147 of the sleeve 145 and the crosspiece 131.

According to one embodiment of the invention, the return element 170 comprises one or more spring(s), for example helical, arranged around the retaining means 140, in particular also around the sleeve 145.

According to one embodiment of the invention, the retaining means 140 comprises a fixing member 154 fixed to the outer end portion 151 of the connecting part 150. The fixing member 154 has a widened section with respect to the end part 151 external. The sleeve 145 is arranged to serve as a stop under the fixing member 154 and comprises for example an internal shoulder 148 to abut under the fixing member 154. According to one embodiment of the invention, the sleeve 145 comprises a cylindrical body 146, for example circular cylindrical, surrounding the intermediate part 153 and connecting the inner shoulder 148 to the outer part 147. According to one embodiment of the invention, the return element 170 bears against an outer face 135 of the crosspiece 131 via a washer 155, which is arranged around the intermediate part 153 of the part 150 of connection. According to one embodiment of the invention, the return element 170 is provided around the cylindrical body 146. According to one embodiment of the invention, the sleeve 145 comprises another cylindrical body 149, for example circular cylindrical, surrounding the intermediate part 153 and located radially under the internal shoulder 148, this other cylindrical body 149 being at a distance from the spacer 120 and able to pass through the washer 155.

According to one embodiment of the invention, the internal end part 152 has a widened section with respect to the intermediate part 153. The projecting part 102 of the retaining base 101 comprises at least a first hooking lug 103 and at least one second hooking lug 104, which are spaced apart, for example in the transverse direction DT, by a gap which is wider than the intermediate part 153 and narrower than the part d internal end 152. To mount the holding device, the intermediate part 153 of the connecting member 150 is thus passed through the gap between the first hooking lug 103 and the second hooking lug 104 and the internal end part 152 is arranged radially under the first tab 103 for attachment and radially under the second tab 104 for attachment. The internal end part 152 thus comes into abutment radially under the first hooking lug 103 and under the second hooking lug 104 to be retained there. Each leg 103, 104 extends for example in length along the axial direction AX.

For example, the connecting piece 150 can be a screw, the head of which forms the internal end part 152 and which has a thread at least on the external end part 151, the fixing member 154 being formed by a nut screwed onto the thread of this screw.

According to one embodiment of the invention, each attachment tab 103, 104 respectively comprises an internal surface 1031, 1041 serving as an abutment on the widened section of the internal end part 152 and an external surface 1032, 1042 serving as abutment under the spacer 120. For example, the internal abutment surface 1031, 1041 and the external abutment surface 1032, 1042 are parallel to the axial direction AX and/or extend circumferentially around the axis AX.

According to one embodiment of the invention, the outer surface 190 of the casing 19 has a determined inclination ANG with respect to the axial direction AX around which the outer surface 190 extends. e 105 of attachment to the outer surface 190.

According to one embodiment of the invention, the hooking lugs 103, 104 (for example the internal abutment surface 1031, 1041 and the external abutment surface 1032, 1042) can for example have an inclination opposite to the inclination determined ANG relative to the part 105, so that the hooking lugs 103, 104 are parallel to the axial direction AX.

According to one embodiment of the invention, the hooking tab 103 is extended by the first front or upstream edge 1033, the hooking tab 104 is extended by the second front or upstream edge 1043. Between the first front edge 1033 and the second front edge 1043 is a space used for the introduction of the intermediate part 153 between these two edges 1033 and 1043. According to one embodiment of the invention, each edge 1033 and 1043 has a determined inclination radially towards the low relative to the tabs 103 and 104, so that the front edge 1033 and 1043 is parallel to the axial direction AX. According to one embodiment of the invention, the gap located between the hooking tabs 103, 104 and the space located between the edges 1033 and 1043 lead to an internal opening 107 for access, making it possible to insert the section widened from the internal end part 152 between the tabs 103, 104, this internal access opening 107 being located between the internal part 105 and the tabs 103, 104.

According to one embodiment of the invention, the support 130 comprises a first sheet 132b and a second sheet 133, which are fixed on either side of the crosspiece 131 and which extend in the axial direction AX. The crosspiece 131 is located in the transverse direction DT between the first sheet 132b and the second sheet 133. The first sheet 132b and the second sheet 133 are used to fix one or more cooling tubes T. For example, several cooling tubes T are fixed, in succession, one behind the other in the axial direction AX, to the first sheet 132b and to the second sheet 133, for example radially below them. For this purpose, the first sheet 132b and the second sheet 133 may comprise indented lower edges 138, 139 of complementary shape to those of the cooling tubes T, in which they are fixed. The cooling tube or tubes T are fixed to the first sheet 132b and to the second sheet 133, for example by brazing. The first sheet 132b and the second sheet 133 are fixed to the crosspiece 131 for example by brazing. For example, the crosspiece 131 has two transverse ends 136 and 137 bent radially outwards, which are fixed flat against the first sheet 132b and the second sheet 133 respectively, for example by brazing.

According to one embodiment of the invention, the first sheet 132b and the second sheet 133 are fixed to several (N) holding devices 100 as described above, such as for example to two holding devices 100 in FIG. The first sheet 132b and the second sheet 133 make it possible to hold a second number M of cooling tubes T, greater than the first number N of holding devices 100 fixed thereto. This reduces the number of points (bases 101) for fixing to the housing 19.

According to one embodiment of the invention, each connecting piece 150 and each spacer 120 are located between two of the cooling tubes T.

According to one embodiment of the invention, the retaining base 101 can be provided on a hole, not shown, which passes through the outer surface 1890 of the casing 19 and which is used when it is free to pass an apparatus of inspection of the inside of the casing 19, this apparatus possibly being of the endoscope type. The retaining base 101 can thus plug this hole.

Of course, the embodiments, characteristics, possibilities and examples described above can be combined with each other or selected independently of each other.

Claims (11)

Device (100) for holding at least one air jet cooling tube (T) extending around an axis (AX), the air jet cooling tube (T) being intended to cool an outer surface (190) of a turbomachine casing (19),
characterized in that the device comprises:
a base (101) intended to be fixed on the outer surface (190) of the casing (19),
a connecting part (150) comprising an outer end part (151), an inner end part (152), which is retained in a projecting part (102) of the base (101), and an intermediate part (153), which is located between the outer end part (151) and the inner end part (152),
a support (130) to which the at least one cooling tube (T) is intended to be fixed, the support (130) comprising a crosspiece (131) having a passage opening (132) through which the intermediate part (153) passes the connecting part (150),
a spacer (120) which extends in a longitudinal direction (DR) and which surrounds the intermediate part (153) of the connecting part (150), the spacer (120) presenting, in a transverse section plane with respect to the longitudinal direction (DR) a width greater than one dimension of the opening (132) so that the spacer (120) bears on the one hand against the crosspiece (131) and on the other hand against the projecting part ( 102),
a retaining means (140), fixed to the outer end part (151) of the connecting piece (150),
a return element (170), which extends between the retaining means (140) and the crosspiece (131) and which is biased in compression towards the crosspiece (131). Device according to Claim 1, characterized in that the retaining means (140) comprises a sleeve (145), which is retained at the outer end part (151) of the connecting part (150) and which comprises at its radially outer end an end portion (147) serving as an abutment for the return element (170), the return element (170) being biased in compression between the end portion (147) of the sleeve (145 ) and the crosspiece (131). Device according to Claim 2, characterized in that the retaining means (140) comprises an enlarged section (154) which is fixed to the outer end part (151) of the connecting piece (150), the sleeve (145 ) is arranged to serve as an abutment (148) against the widened section (154). Device according to Claim 3, characterized in that the connecting piece (150) is a screw, having a head forming the internal end part (152) and a thread at least on the external end part (151),
the retaining means (140) being formed by a nut screwed onto the thread. Device according to any one of the preceding claims, characterized in that a washer (155) for supporting the return element (170) is arranged against an external face of the crosspiece (131) and around the part intermediate (153) of the connecting part (150). Device according to any one of the preceding claims, characterized in that the internal end part (152) has a widened section with respect to the intermediate part (153),
the projecting part (102) of the base (101) comprises at least two hooking lugs (103, 104), which are spaced apart from each other by a gap used for the passage of the intermediate part (153) and against which abuts the widened section of the inner end portion (152). Device according to Claim 6, characterized in that each attachment lug (103, 104) comprises an internal surface (1031, 1041) for abutment against the widened section of the internal end part (152) and an external surface ( 1032, 1042) abutment against the spacer (120). Device according to Claim 7, characterized in that the internal abutment surface (1031, 1041) and the external abutment surface (1032, 1042) extend circumferentially around the axis (AX). Device according to any one of Claims 6 to 8, characterized in that each attachment lug (103, 104) is extended by a respective front edge (1033, 1043), the lugs (103, 104) defining between them a space used for the introduction of the intermediate part (153) along the axis (AX). Device according to any one of the preceding claims, characterized in that the support (130) comprises a first sheet (132b) and a second sheet (133), which are fixed on either side of the crosspiece (131) and which extend axially, a plurality of cooling tubes (T) being fixed in succession axially one behind the other to the first sheet (132b) and to the second sheet (133). Turbomachine for aircraft, comprising a casing (19) having an annular outer surface (190), at least one air jet cooling tube (T), which is intended to cool the outer surface (190) of the casing (19) , at least one holding device (100) according to any one of the preceding claims, fixed to the outer surface (190) of the casing (19) to hold the at least one cooling tube (T) outside the outer surface (190) of the housing (19).