FR3143747A1 - TURBOMACHINE COMPRISING A MEASURING DEVICE ARRANGED BETWEEN A STATOR AND A ROTOR. - Google Patents

Abstract

The invention relates to a turbomachine (1) extending around a longitudinal axis (X) and comprising: - a stator (13, 14), - a rotor (16, 17) driven in rotation around the longitudinal axis (X) relative to the stator (13, 14), and - a parameter measuring device (20) of an aerodynamic flow of the turbomachine, the measuring device (20) comprising a body (21) which extends radially relative to the longitudinal axis and which carries means for recording information (22) relating to the parameters of the flow of the turbomachine (1). According to the invention, the measuring device (20) is connected both to the stator (16, 17) and to the rotor (16, 17) via a freely mounted support ring (30). in rotation relative to the rotor (16, 17) and around the longitudinal axis X. Figure for abstract: Figure 2

Description

TURBOMACHINE COMPRISING A MEASURING DEVICE ARRANGED BETWEEN A STATOR AND A ROTOR. Field of invention

The present invention relates to the general field of aeronautics. It aims in particular at a device for measuring at least one parameter of an aerodynamic flow of a turbomachine, this device being intended to cross an aerodynamic flow of the aircraft turbomachine.

Technical background

As part of the development of turbomachines, and in particular aircraft turbomachines, they undergo a number of tests and trials to verify and validate, on the one hand, their proper functioning and, on the other hand, their ability to maintain their integrity and performance. The validation of these tests and trials makes it possible to obtain certification authorizing their commissioning. In particular, during these tests and trials, measurements of certain aerodynamic flow parameters, such as pressure, temperature and/or acceleration, are carried out using a measuring device.

This measuring device is generally known as an intrusive meter or measuring comb. There are different types that are suitable for measuring one or more flow parameters and that are generally installed in one or more specific zone(s) of the turbomachine where the aerodynamic flow to be measured circulates, such as zones of an aerodynamic vein. These different zones are commonly called "measuring plane". Indeed, the aerodynamic flow circulating in a vein of the turbomachine has different characteristics in various zones of the vein, for example at the level of the central zone of the latter, along the walls delimiting the vein, upstream of stator blades, etc. Several devices may therefore be necessary for a complete mapping of the flow parameters in the vein.

A measuring device comprises an elongated body extending through the aerodynamic flow and equipped with means for recording information relating to the parameters of the flow. Such a device is known for example from documents FR-A1-2 952 713 and FR-A1-3067454. It is known from these examples that the measuring devices are generally fixed to the stator of the turbomachine.

It is possible to fix the measuring devices on a rotor of the turbomachine so as to carry out measurements around this rotor. However, their integration can be compromised. Indeed, the measuring devices fixed to the rotor can generate a force on the parts of the turbomachine. Furthermore, the rotation of the measuring devices at the same time as the rotors can make certain measurements such as pressure unusable, or even impossible.

There is a need to address some or all of the above drawbacks.

The objective of the present invention is to provide a simple and economical solution for carrying out measurements of at least one parameter of a turbomachine aerodynamic flow near a rotor.

We achieve this objective in accordance with the invention by means of a turbomachine extending around a longitudinal axis and comprising:

- a stator,
- a rotor driven in rotation around the longitudinal axis relative to the stator, and
- a device for measuring parameters of an aerodynamic flow of the turbomachine, the measuring device comprising a body which extends radially relative to the longitudinal axis and which carries means for recording information relating to the parameters of the flow of the turbomachine,
the measuring device being connected both on the one hand to the stator and on the other hand to the rotor via a support ring mounted freely rotatable relative to the rotor and around the longitudinal axis.

Thus, this solution makes it possible to achieve the above-mentioned objective. In particular, the support ring mounted freely in rotation in the rotor forms a support for the measuring device and avoids transmitting the forces of the measuring device to the stator. In addition, with such an arrangement, the measuring device is located as close as possible to the rotor (in particular the internal wall of an aerodynamic vein of the turbomachine) to measure the boundary layer without rotating with the rotor.

The turbomachine also includes one or more of the following features, taken alone or in combination:

- the rotor comprises an annular cavity centered on the longitudinal axis and in which a support ring is received.

- guide means are arranged in the annular cavity so as to guide the support ring in rotation.

- the measuring device comprises a lug extending radially at a first end of the body, the lug being intended to be housed in a blind hole of corresponding shape in the support ring.

- the turbomachine comprises an arm fixed on the one hand to a second end of the body in a removable manner and on the other hand to the stator.

- the body comprises a longitudinal cavity passing through the body on either side radially and being intended to receive a fixing rod, the fixing rod being configured so as to fix the arm to the measuring device.

- the lug is formed by a free end of the fixing rod.

- the turbomachine comprises a shim intended to be arranged at the first end of the body and to be crossed by the fixing rod.

- the body comprises a leading edge and a trailing edge opposite each other along the longitudinal axis, the information collection means extending from the leading edge along the longitudinal axis.

The invention further relates to an aircraft equipped with such a turbomachine.

Brief description of the figures

The invention will be better understood, and other aims, details, characteristics and advantages thereof will appear more clearly on reading the detailed explanatory description which follows, of embodiments of the invention given as purely illustrative and non-limiting examples, with reference to the appended schematic drawings in which:

There schematically represents, in axial and partial section, an example of a dual-flow turbomachine to which the invention applies; and

There illustrates in an axial section an example of a measuring device installed in a turbomachine according to the invention.

Detailed description of the invention

There shows an axial and partial sectional view of a turbomachine with longitudinal axis X, in particular a dual-flow turbomachine 1 intended to be mounted on an aircraft. Of course, the invention is not limited to this type of turbomachine and can be a single-flow turbojet or a turboprop equipped with a single unducted propeller or a pair of unducted, counter-rotating propellers.

Turbomachine 1 of the comprises, in a conventional manner and from upstream to downstream, a fan 2, a low-pressure compressor 3, a high-pressure compressor 4, an annular combustion chamber 5, a high-pressure turbine 6, a low-pressure turbine 7. An exhaust nozzle 8 is advantageously arranged downstream of the low-pressure turbine 7. The high-pressure compressor 4 and the high-pressure turbine 6 are connected by a high-pressure shaft and form with it a high-pressure (HP) body. The low-pressure compressor 3 and the low-pressure turbine 7 are connected by a low-pressure shaft and form with it a low-pressure (LP) body.

In the present invention, the terms “upstream” and “downstream” are defined in relation to the circulation of gases in the turbomachine and here along the longitudinal axis X. Similarly, the terms “radial”, “internal” and “external” are defined in relation to a radial axis Z perpendicular to the longitudinal axis X and with regard to the distance from the longitudinal axis X.

The turbomachine 1 comprises a first annular vein, called the primary vein 9, in which a primary aerodynamic flow or hot flow circulates and a second annular vein, called the secondary vein 10, in which a secondary aerodynamic flow or cold flow circulates around the primary vein 9. The primary flow passes through the compressors, the combustion chamber, and the turbines, then opens into the nozzle 8 towards the atmosphere.

The primary and secondary veins 9, 10 are coaxial. In particular, the primary vein 9 is delimited radially by an annular internal casing 11 and an inter-vein casing 12 surrounding the internal casing 11. As for the secondary vein 10, the latter is delimited radially by the inter-vein casing 12 and an annular external casing 13 to which a fan casing 14 is secured. The latter surrounds the blades 15 of the fan 2.

The turbomachine 1 comprises at least one device 20 for measuring parameters of an aerodynamic flow which is designed to measure one or more parameters of the flow circulating in the turbomachine 1 so as to establish a map of the pressures, temperatures, accelerations, and/or the composition of said flow in the vicinity of the measuring device 20. These parameters are necessary to obtain certification of the turbomachine before its marketing for example or to check the state of health of the turbomachine. The measurement is said to be intrusive because it is carried out directly in the flow of the flow.

Advantageously, the measuring device 20 is intended to be installed substantially radially in one of the primary and secondary veins of the turbomachine.

According to yet another advantageous characteristic, the measuring device 20 is arranged upstream of the fan 2. Advantageously, the measuring device 20 is arranged along the radial axis and transversely to the flow of the air flow entering the turbomachine.

In reference to the , the measuring device 20 comprises a body 21 and information recording means 22 configured to record information relating to at least one parameter of the flow flowing in the turbomachine.

Preferably, the measuring device 20 is configured to measure the pressure of the flow.

The body 21 is elongated and extends in a direction of elongation A between a first end 21a and a second end 21b. As we can also see in the , the body 21 has a leading edge 24a and a trailing edge 24b opposite transversely to the direction of elongation A. The leading edge 24a and the trailing edge 24b respectively connect two lateral faces (not shown) opposite in a transverse direction. This direction is perpendicular to the direction of elongation (and parallel to the longitudinal axis X in the installation situation in the turbomachine).

The body 21 may have an oblong cross-section or, alternatively, a NACA (National Advisory Committee for Aeronautics) type cross-section. In the latter case, the opposite side faces thus meet at an edge at the trailing edge 24b.

The body 21 of the measuring device 20 advantageously carries the information recording means 22. These extend transversely to the direction of elongation of the body and here parallel to the longitudinal axis X (and to the flow of the air flow).

On the , the information collection means 22 are arranged at the leading edge 24a of the body 21. These are also arranged and distributed regularly along the leading edge 24a (either along the radial axis Z or along the direction of elongation of the body). The information collection means 22 are advantageously connected to means (not shown) for conveying the information collected by the information collection means 22.

The turbomachine 1 is advantageously equipped with an information processing system 50 which is illustrated in the schematically. The information processing system 50 is connected to the routing means.

In the present example, the information collection means 22 comprise nozzles 25. Each nozzle 25 has a substantially cylindrical shape and extends from the leading edge 24a. The nozzles 25 are regularly distributed along the leading edge 24a. Each nozzle 25 communicates with a longitudinal cavity 26 arranged in the body 21 of the measuring device 20. The longitudinal cavity 26 passes through the body 21 of the measuring device 20 on either side and at the first and second ends 21a, 21b. Each nozzle 25 comprises an inlet orifice which is exposed to the aerodynamic flow to take a sample therefrom.

In the present exemplary embodiment, the measuring device 20 is connected both to a stator of the turbomachine and to a rotor of the turbomachine. The rotor is driven in rotation about the X axis relative to the stator.

The stator of the turbomachine is advantageously a casing of the turbomachine such as the fan casing 14 or the external casing 13 (or nacelle carried by the fan casing). In the case of a test bench, the measuring device 20 could be connected to a frame of the test bench or to a wall (or wall) of a wind tunnel.

The rotor of the turbomachine is advantageously formed of a rotating shroud whose external surface delimits an aerodynamic vein. The rotating shroud is driven by a rotor shaft (such as the low pressure shaft). Advantageously, the rotor of the fan is formed of the rotor of the fan. Advantageously, the fan rotor comprises a hub 16 and a cone 17.

In particular and as represented on the , the hub 16 is centered on the longitudinal axis X. The hub 16 carries a series of fan blades 15 which are regularly distributed around the longitudinal axis X. Each blade 15 extends radially from the hub 16 outwardly. The free ends 15a (shown in the ) blades 15 are opposite the fan casing 14.

Still referring to the , the cone 17 is integral in rotation with the hub 16. The cone 17 is mounted upstream of the hub and covers it. Advantageously, the cone 17 is centered on the longitudinal axis and has an axisymmetric shape.

Advantageously, the rotor (here the cone and the hub or the rotating shroud) is driven in rotation relative to the measuring device 20. For this, the turbomachine is advantageously equipped with a support ring 30 which is mounted free to rotate relative to the rotor. The support ring is configured so that the measuring device 20 bears on the rotor.

According to this exemplary embodiment, the support ring 30 is centered on the longitudinal axis X and rotates freely about the longitudinal axis X. This support ring 30 is interposed between the rotor parts and has a free movement independent of the rest of the rotor.

The rotor comprises an annular cavity 31 centered on the longitudinal axis and in which the support ring 30 is received.

Rotational guide means 32 make it possible to guide the support ring 30 in rotation relative to the rotor.

Advantageously, but not limitingly, the annular cavity 31 is formed by a portion of the cone 17 and by a portion of the hub 16. The annular cavity 31 opens onto a radially external surface 33 of the fan rotor.

Advantageously, but not limited to, the support ring 30 has an axial section in the shape of an inverted T. In particular, the support ring 30 comprises two opposite branches 30a and a leg 30b extending transversely to the branches 30a. The annular cavity 31 has a corresponding shape (i.e. an inverted T).

The guide means 32 comprise rolling bearings 34. Alternatively, the guide means comprise lubricated smooth rings or magnetic bearings. The nature of the guide means can be defined according to the rotation speed and the dimensions (for example diameter) of implantation.

In the present example, two rolling bearings 34a, 34b are arranged in the annular cavity 31. Each rolling bearing 34a, 34b comprises an inner ring 35a secured to one of the branches 30a. Each rolling bearing comprises an outer ring 35b secured to an annular bearing surface 36 of the rotor. Each rolling bearing 34 comprises rolling members which are here balls. There is a rolling bearing on each side of the leg 30b of the support ring 30.

The measuring device 20 comprises a lug 37 which is mounted in a corresponding housing 38 of the support ring 30. In this way, during rotation of the fan rotor here, the support ring 30 is not driven in rotation and the measuring device 20 is stationary in rotation. The lug 37 also allows the measuring device 20 to be positioned as close as possible to the rotor and to guarantee the position of the information recording means 22 relative to the air flow.

The lug 37 advantageously extends from the first end 21a of the body 21 and along the direction of elongation A of the body. In the present example, the direction of elongation A is parallel to the radial axis Z. The lug 37 is intended to be slidably housed in the hole 38 of corresponding shape in the support ring 30. The hole 38 extends along the radial axis. Advantageously, the hole 38 is blind.

On the , an arm 40 or pole makes it possible to connect the stator to the measuring device 20. The arm 40 acts as a support means for the measuring device 20 and so that the latter is as close as possible to the rotor.

Advantageously, but not limited to, the arm 40 comprises a first end 40a which is fixed to the second end 21b of the body 21 of the measuring device 20. The arm 40 also comprises a second end 40b which is fixed to the stator. The second end 40b is removably fixed by means of fixing members 41 such as screws, nuts. This makes it easier to disassemble or assemble for maintenance of this arm and even of the measuring device.

The first end 40a is advantageously removably fixed to the body 21 of the measuring device 20. The fixing is carried out using fixing members. An example of a fixing member is a fixing rod 42. The latter is advantageously received in the longitudinal cavity 26. In this way, it is also possible to easily mount and dismount the measuring device 20 alone for its maintenance.

According to yet another advantageous characteristic, the rod 42 passes through the body 21 on either side. The free end of the fixing rod forms the lug 37. The rod 42 can be a screw.

The arm 40 is not aligned with at least the measuring device (angularly offset, not in the same plane) in order to less disturb the measurement by an obstacle in the flow in the measurement zone.

Advantageously, a shim 43 is intended to be arranged towards the first end 21a of the body 21 of the measuring device 20. Such a shim 43 makes it possible to modify or adjust the height of the measuring device 20 along the radial axis. Advantageously, the shim 43 is crossed on either side by a through-hole 44. In the installation position, the axis of the through-hole 44 is centered on the direction of elongation A and the radial axis Z. The fixing rod 42 passes through the shim 43. Advantageously, the through-hole 44 is tapped so that the shim 43 is screwed onto the fixing rod 42.

Thus, such a configuration makes it possible to place the measuring device 20 as close as possible to the rotor and without disturbing the aerodynamic flow to be measured and without transmitting forces to the stator to which the measuring device is fixed.

Claims (10)

Turbomachine (1) extending around a longitudinal axis (X) and comprising:
- a stator (13, 14),
- a rotor (16, 17) driven in rotation about the longitudinal axis (X) relative to the stator (13, 14), and
- a device (20) for measuring parameters of an aerodynamic flow of the turbomachine, the measuring device (20) comprising a body (21) which extends radially relative to the longitudinal axis and which carries means for recording information (22) relating to the parameters of the flow of the turbomachine (1),
characterized in that the measuring device (20) is connected both on the one hand to the stator (16, 17) and on the other hand to the rotor (16, 17) via a support ring (30) mounted free to rotate relative to the rotor (16, 17) and around the longitudinal axis X. Turbomachine (1) according to the preceding claim, characterized in that the rotor (13, 14) comprises an annular cavity (31) centered on the longitudinal axis (X) and in which a support ring (30) is received. Turbomachine (1) according to the preceding claim, characterized in that guide means are arranged in the annular cavity (31) so as to guide the support ring (30) in rotation. Turbomachine (1) according to one of the preceding claims, characterized in that the measuring device (30) comprises a lug (37) extending radially at a first end (21a) of the body (21), the lug (37) being intended to be housed in a blind hole of corresponding shape of the support ring (30). Turbomachine (1) according to one of the preceding claims, characterized in that it comprises an arm (40) fixed on the one hand to a second end (21b) of the body (21) in a removable manner and on the other hand to the stator (13, 14). Turbomachine (1) according to the preceding claim, characterized in that the body (21) comprises a longitudinal cavity (26) passing through the body (21) on either side radially and being intended to receive a fixing rod (41), the fixing rod (41) being configured so as to fix the arm (40) to the measuring device (30). Turbomachine (1) according to claims 4 and 6, characterized in that the lug is formed by a free end of the fixing rod (41). Turbomachine (1) according to one of the preceding claims, characterized in that it comprises a shim (43) intended to be arranged at the first end (21a) of the body (21) and to be crossed by the fixing rod (42). Turbomachine (1) according to one of the preceding claims, characterized in that the body (21) comprises a leading edge (24a) and a trailing edge (24b) opposite along the longitudinal axis, the information recording means (22) extending from the leading edge (24a) along the longitudinal axis. Aircraft comprising a turbomachine (1) according to any one of the preceding claims.