Device for implanting a probe in the flow stream of a turbomachine, turbomachine comprising such a device and method for installing this device
The probe implantation device with a radial support and fastening elements addresses the challenge of installing probes in turbofan engines by providing secure and accessible installation, enhancing data acquisition in turbofan engines.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Patents
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2022-05-09
- Publication Date
- 2026-06-19
Smart Images
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Abstract
Description
Title of the invention: Device for implanting a probe in the flow of a turbomachine, turbomachine comprising such a device and method for installing this device. TECHNICAL FIELD OF THE INVENTION
[0001] The present invention relates to a device for implanting a probe in the primary flow of a turbofan engine. It also relates to a turbofan engine equipped with this device and to a method for installing this device in the primary flow of the turbofan engine.
[0002] The invention finds applications in the field of aeronautics and, in particular, in the field of data acquisition for characterizing the aerodynamic flow circulating in a turbomachine duct. TECHNOLOGICAL BACKGROUND OF THE INVENTION
[0003] Aircraft turbofan engines generally have a primary and a secondary flow in which gas flows circulate. An intermediate casing is usually arranged in a generally axial manner between the primary and secondary flows. To improve the performance of the turbofan engine, it is important to measure various data characterizing the gas flows circulating in the turbofan engine's flows.
[0004] Turbomachinery manufacturers are particularly interested in measuring pressure and temperature data of the gas flow circulating in the primary stream. To perform these measurements, it has been considered to implant one or more probes, for example a PTTT probe (total pressure and temperature probe), inside the primary stream. Implanting a probe in the primary stream requires fixing said probe to the intermediate housing so that the probe extends radially within the primary stream. It has therefore been considered to fix the probe to an axial surface of the intermediate housing. An example of an axial surface that can accommodate a probe is shown in [Fig. 1]. This [Fig. 1] shows a portion of an intermediate housing 10 having an axial surface 11, that is to say, a surface extending circumferentially along the central axis XX of the turbomachine.
[0005] It was considered to fix the probe to this axial surface 11 by means of a boss formed on the axial surface 11 of the intermediate housing 10. However, the intermediate housing 10 is a single-piece casting. The boss would therefore have to be made by machining an extra thickness 12 of the casting 10. However, passing a tool into the area where the axial surface 11 is located is completely impossible because the environment is narrow and difficult to access. No tool can therefore be introduced into this environment. ronnement to machine the excess thickness 12. Summary of the invention
[0006] To meet, on the one hand, the needs for installing a probe in the primary flow of the turbomachine and, on the other hand, the problems of machining an extra thickness of the intermediate casing to fix the probe, the applicant proposes to implant a probe in the primary flow by means of an implantation device comprising a probe support fixed on a radial surface of the casing and provided with a cavity in which the probe is housed.
[0007] According to a first aspect, the invention relates to a device for implanting a probe in a primary flow of a turbofan engine, comprising a support fixed to a radial surface of an intermediate housing disposed between the primary flow and a secondary flow, said support comprising: a radial cavity in which the probe is housed, at least one radial opening in which a fastening element is mounted to secure the probe to the support, and at least one axial hole in which an anchoring element is mounted to fix the support to the intermediate housing.
[0008] This probe mounting device has the advantage of being able to be fixed to a radial surface of the intermediate housing, this radial surface being accessible for machining from the outside of said housing. The radial surface of the intermediate housing can therefore be machined so that a support can be fixed to it, and the probe can be installed and secured in this support.
[0009] In addition to the characteristics mentioned in the preceding paragraph, the probe implantation device according to one aspect of the invention may have one or more additional characteristics from among the following, considered individually or in all technically possible combinations: The support has two radial openings, positioned on either side of the radial cavity and each receiving a fixing element. The support has two axial holes, positioned on either side of the radial cavity and / or radial holes, each receiving an anchoring element. The fixing element includes a screw. The anchoring element consists of a transverse axis and a nut.
[0010] A second aspect of the invention relates to a double-flow turbomachine, comprising an intermediate casing disposed between a primary and a secondary flow of said turbomachine, characterized in that it comprises: a probe extending radially into the primary vein, and • a probe implantation device as defined above.
[0011] This turbomachine has the advantage of integrating one or more probes measuring data relating to the gas flow of the primary stream, this data being able to be transmitted to a data acquisition unit.
[0012] The turbomachine 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: • the intermediate housing has at least one slot machined in a radial surface of said intermediate housing to receive an anchoring element. • the radial surface of the intermediate housing has a concavity in which the support is partially housed. • it includes a casting hole formed at a junction between the radial surface and an axial area of the intermediate housing, the probe being partially housed in said casting hole.
[0013] A third aspect of the invention relates to a method for installing a probe implantation device in the primary flow of a double-flow turbomachine as defined above, comprising the following operations: • machining of at least one slot in a radial surface of the intermediate housing, • mounting an anchoring element in the light, • Installation of the previously defined mounting device against the radial surface and fitting of the axial opening of the support onto the anchoring element, • Installation of the probe in the radial cavity of the support and securing the fixing element in the radial hole of the support, and • Connecting the probe's electrical wiring to a data acquisition unit. BRIEF DESCRIPTION OF THE FIGURES
[0014] Other advantages and features of the invention will become apparent from the following description, illustrated by the figures in which:
[0015] Fig. 1, already described, represents a local perspective view of a portion of the intermediate casing of a double-flow turbomachine;
[0016] Fig. 2 schematically represents a cross-sectional view of a portion of a dual-flow turbomachine equipped with the probe implantation device according to the invention;
[0017] Fig. 3 schematically represents a cross-sectional view of the device for implanting a probe according to the invention in a dual-flow turbomachine;
[0018] Figure 4 schematically represents a top view of the device implantation of a probe according to the invention in a double-flow turbomachine; and
[0019] The [Fig.5] schematically represents different stages of the process of installing the probe implantation device according to the invention. DETAILED DESCRIPTION
[0020] An example of an embodiment of a probe implantation device and a method for installing this device is described in detail below, with reference to the accompanying drawings. This example illustrates the features and advantages of the invention. It should be noted, however, that the invention is not limited to this example.
[0021] In the figures, identical elements are identified by identical reference numerals. For the sake of readability, the size scales between represented elements are not respected.
[0022] An example of a turbofan engine is shown, in a partial cross-sectional view, in [Fig. 2]. This turbofan engine 100, more simply called a turbofan engine, has an intermediate casing 110, more simply called a casing, positioned between a primary flow 120 and a secondary flow 130 of the turbofan engine. A gas flow, called the primary flow, circulates in the primary flow 120 through compressors, a combustion chamber, and turbines. Another gas flow, called the secondary flow, circulates in the secondary flow 130, around the primary flow, and mixes with this primary flow at the turbine outlet.
[0023] At least one probe 140 is installed in the primary flow 120 to measure data relating to the primary flow. The probe 140 is fixed to the housing 110 by means of an implantation device 150 and extends radially in the primary flow 120. This probe 140 can be, for example, a PTTT probe used to measure pressure and temperature data of the primary flow. The measured data are, for example, the total pressure, which measures the flow velocity in the primary flow, and the total temperature, which measures the flow temperature; this data is used to determine, for example, the performance of the high-pressure compressor module.
[0024] An example of a probe mounting device 150 is shown in a cross-sectional side view in [Fig. 3] and in a top view in [Fig. 4]. The probe mounting device 150 includes a probe support 155 designed, on the one hand, to receive the probe 140 and, on the other hand, to be fixed to a radial surface 115 of the intermediate housing 110. This support 155 includes: • one or more radial cavities 156 designed to receive one or more probe(s) 140, • one or more radial orifices 157 designed to each receive a fastening element 142, and • one or more axial orifice(s) 158 designed to each receive an anchoring element 152.
[0025] The support 155 is metallic and monobloc. It can take various forms, for example, a rectangular prism shape, a semi-ellipsoidal shape, or any other shape provided that it is adapted to include at least one radial cavity, at least one radial orifice and at least one axial orifice.
[0026] Depending on the type of probe 140 to be held, the radial cavity 156 may be a through-hole, which passes radially through the support 155, or a blind opening. For example, in the case of a PTTT probe, the radial cavity 156 is a through-hole allowing the probe 140 to be fixed in the support 155 while extending into the primary vein 120. For other types of probes, a blind cavity, for example with a lateral window, may be sufficient to allow the probe to perform the desired measurements.
[0027] The radial orifices 157 are orifices arranged at a distance from each other and which pass radially through the support 155 to allow the probe 140 to be fixed to the support 155. These radial orifices may, for example, be two in number, a radial orifice 157 being positioned on either side of the radial cavity 156.
[0028] The axial holes 158 are holes arranged at a distance from each other and which pass axially through the support 155 to allow the support to be fixed to the radial surface 115 of the housing 110. These axial holes 158 may, for example, be two in number, one axial hole 158 being positioned at each end of the support 155, for example on either side of the radial holes 157. These axial holes 158 are designed to be positioned opposite two holes 118 machined in the radial surface 115 of the housing 110. Indeed, to allow the support 155 to be fixed to the radial surface 115 of the housing, holes 118 are formed in line with the radial holes 158. These holes 118, for example tapped holes, may to be formed by machining, after manufacture of the housing 110, at the time of installation of the support 155, so that said orifices 118 are correctly aligned with the radial orifices 158.This machining operation is easily performed using a machining tool because the tool can be brought to the radial surface 115 from the outside of the housing (unlike the prior art where the machining tool had to access it from the inside of the housing). An operator thus accesses the radial surface 115 to be machined via the outside of the housing.
[0029] The support 155 is fixed to the radial surface 115 of the housing 110 by means of at least one anchoring element 152, this anchoring element 152 comprising, for example, a transverse shaft 152a and a nut 152b mounted at the end of said transverse shaft. The probe 140 is fixed to the support 155 by means of at least one fastener 142, this fastener 142 being, for example, a screw.
[0030] In the example of Figures 3 and 4, the support 155 has a shape substantially like a rectangular prism with a central swollen area 155a in which the radial cavity 156 is positioned. Two radial ports 157 are positioned laterally on either side of the radial cavity 156. Two axial ports 158 are positioned laterally on either side of the two radial ports 157, each axial port 157 being located at one end of the rectangular prism. In this example, the support 155 is fixed to the radial surface 115 of the housing 110 by means of two anchoring elements 152, and the probe 140 is fixed to the support 155 by means of two fastening elements 142.
[0031] In certain embodiments, depending on the dimensions of the probe 140, a concavity 116 may be provided in the radial surface 115 of the housing 110. Indeed, if the dimensions of the probe 140 are relatively large compared to the gap E in which the implantation device 150 is installed, it is possible to provide a concavity 116, or a notch, in the radial surface 115 on which the support 155 is fixed in order to offer a spacing better adapted to the dimensions of the implantation device and the probe. This concavity 116 can consist of a casting radius formed during the molding of the housing 110. In these embodiments, the concavity 116 allows to accommodate in part the central swollen area 155a of the support 155, which reduces the bulk of the implantation device 150 in the gap E.
[0032] In certain embodiments, for example when the radial surface 115 is not sufficiently large to allow the complete installation of the implanting device 150 and the probe 140, a casting hole 117 may be provided in an axial area 119, which extends substantially perpendicularly to the radial surface 115, or at the junction of the radial surface 115 and the axial area 119. This casting hole 117, located opposite the radial cavity 156 of the support 155, forms a passage for the probe 140 so that it can extend inside the primary channel 120. As with the concavity 116, the casting hole 117 may be formed during the manufacture of the housing 110.
[0033] In these embodiments with casting hole 117, a sealing gasket 160 can be mounted around said casting hole 117, between the axial zone 119 and the support 155.
[0034] The implantation device 150 can be installed in the turbomachine 100 by following a series of operations shown in [Fig. 5]. The method for installing the implantation device 150 of the probe 140 can, for example, include a first operation (designated step A in [Fig. 5]) of manufacturing a housing 110 equipped, if necessary, with a casting hole 117 and / or a concavity 116. The method then includes a second operation (step B) of machining at least one slot 118 in the radial surface 115 of the housing. In the example of [Fig. 5], the second The operation consists of machining two holes 118 located opposite the axial holes 158 of the support 155. A third operation (step C) then consists of mounting an anchoring element 152, in particular a transverse shaft, in each of the holes 118. This third operation may also include installing the seal 160 around the casting hole 117, in embodiments where such a casting hole 117 exists. The installation process may include a separate operation of manufacturing a support 155 as described previously. This support 155 is installed against the radial surface 115 during a fourth operation (step D of [Fig. 5]). This installation operation of the support 155 includes not only the positioning of the support 155 but also the fitting of the axial holes 158 onto the transverse axes of the anchoring elements 152 and then the locking of the support 155 against the radial surface 115 by means of the nuts 152b of the anchoring elements 152.Indeed, once the nuts 152b are screwed onto the ends of the transverse shafts 152a, the bracket 155 is fixed and locked onto the housing 110. A fifth operation (step E in [Fig. 5]) can then be carried out. This fifth operation involves installing the probe 140 in the radial cavity 156 of the bracket 155 and mounting the fasteners 142 through a base 145 of the probe 140 and the radial holes 157 of the bracket 155. Once these fasteners 142, for example screws, are in place in the radial holes 157, the probe is installed and fixed onto the bracket 155. Electrical wiring can then be connected to electrical connection elements 146 of the probe 140 in order to electrically connect said probe 140 to a data acquisition unit mounted externally on the housing 110.This data acquisition unit, not shown in the figures, processes all or part of the data measured in the turbomachine and, in particular, the data measured by probe 140 within the primary vein 120.
[0035] Although described through a number of examples, variants and embodiments, the probe implantation device according to the invention, and its installation method, include various variants, modifications and improvements which will be obvious to a person skilled in the art, it being understood that these variants, modifications and improvements are part of the scope of the invention.
Claims
Demands
1. Device for implanting (150) a probe (140) for measuring data relating to a primary flow in a primary vein (120) of a dual-flow turbomachine (100), comprising a support (155) fixed on a radial surface (115) of an intermediate housing (110) disposed between the primary vein and a secondary vein (130), said support comprising: - a radial cavity (156) in which the probe is housed, - at least one radial orifice (157) in which a fixing element (142) is mounted for fixing the probe on the support, and - at least one axial orifice (158) in which an anchoring element (152) is mounted for fixing the support on the intermediate housing.
2. Device according to claim 1, characterized in that the support (155) has two radial orifices (157), positioned on either side of the radial cavity (156) and each receiving a fixing element (142).
3. Device according to claim 2, characterized in that the support (155) has two axial orifices (158), positioned on either side of the radial cavity (156) and / or radial orifices (157) and each receiving an anchoring element (152).
4. Device according to any one of claims 1 to 3, characterized in that the fastening element (142) comprises a screw.
5. Device according to any one of claims 1 to 4, characterized in that the anchoring element (152) comprises a transverse axis (152a) and a nut (152b).
6. A double-flow turbomachine (100), comprising an intermediate casing (110) disposed between a primary flow (120) and a secondary flow (130) of said turbomachine, characterized in that it comprises: - a probe (140) extending radially in the primary flow, and - a probe implantation device (150) according to any one of claims 1 to 5.
7. Turbomachine according to claim 6, characterized in that the intermediate casing (110) has at least one orifice (118) machined in a radial surface (115) of said intermediate housing to receive an anchoring element (152).
8. Turbomachine according to claim 7, characterized in that the radial surface of the intermediate housing has a concavity in which the support is partially housed.
9. Turbomachine according to claim 8, characterized in that it comprises a casting hole (117) formed at a junction between the radial surface (115) and an axial zone (119) of the intermediate housing, the probe (140) being partially housed in said casting hole.
10. A method for installing a probe implantation device in the primary flow of a turbofan engine according to any one of claims 6 to 9, comprising the following operations: - machining (step B) of at least one opening (118) in a radial surface (115) of the intermediate housing, - mounting (step C) of an anchoring element (152) in the opening (118), - installing (step D) the implantation device (150) according to any one of claims 1 to 5 against the radial surface and fitting the axial opening (158) of the support (155) onto the anchoring element, - installing (step E) the probe (140) in the radial cavity (156) of the support and securing the fixing element (142) in the radial opening (157) of the support, and - connecting electrical wiring for the probe (140) to a unit data acquisition.