WO2021191529A1

WO2021191529A1 - Dynamic sealing device for a turbomachine probe

Info

Publication number: WO2021191529A1
Application number: PCT/FR2021/050445
Authority: WO
Inventors: Jean-Louis Champion-Reaud; Nicolas ZOULOUMIAN; Jean-Luc BREINING; Paul Henri Joseph Mauclair; Carlos Mendes; David LE-VOT; Cyril COBOS
Original assignee: Safran
Priority date: 2020-03-25
Filing date: 2021-03-18
Publication date: 2021-09-30
Also published as: FR3108653A1; FR3108653B1

Abstract

The invention relates to a dynamic sealing device (220) for a measuring system (200) comprising a measuring probe (210) intended to pass through a first motor compartment (140) of a turbomachine and to measure a physical variable in a second motor compartment (150), the first motor compartment (140) being defined in its radially outer portion by an outer casing (120) and in its radially inner portion by an inner casing (130), the second motor compartment (150) being defined in its radially outer portion by the inner casing (130), the dynamic sealing device (220) being characterised in that it comprises: a first body (230) configured to be positioned inside the first motor compartment (140) and secured to the outer casing (120); a second body (240) configured to be positioned inside the first motor compartment (140) and secured to the inner casing (130), the first body (230) and the second body (240) defining a passage (205) inside the first motor compartment (130) for inserting the measuring probe (210); a first sealing means (250) configured to provide a movable and sealed connection between the first body (230) and the second body (240); a second sealing means (260) formed inside the passage (205) configured to cooperate with the measuring probe (210) and to ensure a seal between the two ends of the passage (205) formed by the first body (230) and the second body (240).

Description

DESCRIPTION

TITLE: DYNAMIC SEALING DEVICE FOR PROBES

TURBOMACHINE

TECHNICAL FIELD OF THE INVENTION

[0001] The technical field of the invention is that of the characterization of a turbomachine in the development phase as well as the exploration and measurement of the flow flows within a turbomachine.

[0002] The invention relates more particularly to a dynamic sealing device allowing the introduction as well as the displacement of a measurement probe in a flow duct of a turbomachine, and capable of ensuring a seal between different aerothermal conditions d 'a turbomachine.

[0003] The invention finds a particularly advantageous application in the field of test turbomachines.

TECHNICAL BACKGROUND

[0004] Nowadays, the development or improvement phase of a turbomachine is largely based on the results of increasingly sophisticated and efficient digital codes or software. In the field of aeronautics, however, it is necessary to carry out, in addition, so-called "readjustment" operations of these digital codes and software with measurements on test turbomachines in order to improve their predictive nature. Such readjustment operations allow substantial savings in time and money in the initial stages of turbine engine development.

[0005] These “readjustments” can only be envisaged by means of unsteady data collected within the turbomachine itself, in order to take into account all the phenomena of aerodynamic / thermal / mechanical coupling of which the turbomachine is the seat, such as particularly the high pressure turbine.

[0006] However, the measurement of any quantity (for example of pressure, speed, temperature, concentration, etc.) within an internal flow of the turbomachine by means of an intrusive probe is made complex and delicate by: the aerothermal environment of the probe; in particular by the high pressure and temperature levels within the flow in question; the confinement associated with the increasingly important compactness of turbomachines; the crossing of multiple watertight walls delimiting different aerothermal environments with different pressures, temperatures and concentrations; the need to achieve effective sealing at each interface of the turbomachine delimiting often very different aerothermal conditions (for example between an internal vein and an external vein of a bypass turbomachine) so as not to degrade its operation; the control of the radial and axial differential expansions of the various parts which can be important, during the operational phases, and in particular during the thermal transients.

SUMMARY OF THE INVENTION [0007] In this context, the invention aims to provide a dynamic sealing device configured to allow the introduction of a measurement probe into a flow of a turbomachine, while preserving the integrity. different internal flows of the turbomachine, despite very different air-thermal conditions at the interfaces, compatible with the geometrical constraints of current compact turbomachines, allowing a radial displacement of the measurement probe and making it possible to absorb the differential expansions between stator-stator or else stator-rotor.

To this end, the invention relates to a dynamic sealing device for a measuring system comprising a measuring probe intended to pass through a first engine compartment of a turbomachine and to measure a physical quantity in a second engine compartment, the first engine compartment being delimited in its radially outer portion by an outer casing (and in its radially inner portion by an inner casing, the second engine compartment being delimited in its radially outer portion by said inner casing, said dynamic sealing device according to the invention being characterized in that it comprises: a first body configured to be positioned inside said first engine compartment and secured to the outer casing, a second body configured to be positioned inside said first engine compartment and secured to the internal casing, the first body and the second body delimiting a passage inside the first engine compartment for the introduction of said measurement probe; a first sealing means configured to provide a movable and sealed connection between the first body and the second body ; a second sealing means formed inside said passage configured to cooperate with said measurement probe re and to ensure a seal between the two ends of said passage formed by said first body and said second body.

[0009] In the present application, the term probe will denote any means making it possible to carry out a measurement of a physical quantity (such as for example pressure, temperature, particle concentration, speed, etc.) that it is intrusive such as than a thermocouple or an anemoclinometric probe, or even a non-intrusive one, such as a light beam (laser, IR, UV, etc.). In both cases, the measuring means, hereinafter referred to by the general term "probe", travels inside a tube formed by a sheath opening into a flow vein. The probe can be fixed or mobile, that is to say set in motion by a device controlled manually or automatically.

The dynamic sealing device is understood to mean a sealing device allowing the radial displacement (relative to the engine axis of a turbomachine) of a probe and allowing the radial and axial expansions inherent in the operating conditions of a turbomachine. The invention advantageously makes it possible to achieve a seal between two compartments of a turbomachine having high and different temperature and pressure conditions, while allowing the differential expansions of the parts of the turbomachine and by allowing movement of the probe. measurement so as to allow a radial exploration of a flow vein if necessary.

The invention finds a particularly interesting application in the field of tests, such as engine tests or partial tests relating to the exploration of flows, reactive or inert, from the air inlet to the exhaust nozzle.

[0013] The dynamic sealing device according to the invention advantageously makes it possible to ensure simultaneously: sealing under severe pressure and temperature conditions relating to the operation of a turbomachine; correction of the axial and / or radial differential expansions of the housings with respect to one another; radial displacement of the probe so as to allow different radial positions of the measurement probe for radial exploration of a turbomachine flow vein.

[0014] In addition to the characteristics mentioned in the previous paragraph, the dynamic sealing device according to the invention may have one or more additional characteristics among the following, considered individually or in any technically possible combination.

Advantageously, the first sealing means is housed in an annular housing provided at said first body, said first sealing means ensuring sealed contact with said second body.

Advantageously, the first sealing means is housed in an annular housing provided at said second body, said first sealing means ensuring sealed contact with said first body. Advantageously, the annular housing is provided at one end of said first body or at one end of said second body.

Advantageously, the first sealing means is movable axially and radially with respect to the axis of the turbomachine in said annular housing. Advantageously, the first sealing means is a segment seal.

Advantageously, said second sealing means has an orifice for the passage of said measurement probe, said orifice having a diameter configured to ensure sealed contact with said measurement probe and to allow relative movement of said measurement probe. . Advantageously, said second sealing means is housed in a housing provided at said first body or at said second body.

Advantageously, said second sealing means is movable axially and radially with respect to the axis of the turbomachine, in said housing.

A subject of the invention is also a measuring system for measuring a physical quantity inside an engine compartment of a turbomachine, said measuring system comprising: a measuring probe intended to pass through a first engine compartment of a turbomachine and measuring a physical quantity in a second engine compartment; a dynamic sealing device according to the invention.

The invention also relates to a bypass turbomachine comprising a measuring system according to the invention for measuring a physical quantity inside a primary flow stream of a primary flow at the means of a measuring probe passing through a secondary flow vein of secondary flow.

The invention and its various applications will be better understood on reading the following description and on examining the accompanying figure. BRIEF DESCRIPTION OF THE FIGURES

[0026] [Fig. 1] is a block diagram illustrating the dynamic sealing device according to the invention through which a measurement probe passes.

[0027] Figure 1 is shown only as an indication and as an example and is not therefore limiting of the invention.

DETAILED DESCRIPTION

In the present application, the terms "upstream" and "downstream" are defined relative to the normal direction of gas flow (from upstream to downstream) through a turbomachine. Also called "axis of the turbomachine" or "engine axis", the axis of rotation of a rotor of the turbomachine. Unless otherwise indicated, an “axial” direction corresponds to the direction of the axis of the turbomachine and a “radial” direction is a direction perpendicular to the axis of the turbomachine and intersecting this axis. Likewise, an axial plane is a plane containing the axis of the turbomachine, and a radial plane is a plane perpendicular to this axis.

Unless otherwise specified, the adjectives "lower", "internal",

"Outer", "outer" are used in the present application with reference to a radial direction so that the inner part of an element is, in a radial direction, closer to the axis of the turbomachine than the outer part of the same element.

In a double-flow turbomachine, the inlet air flow is separated at the level of the fan into a primary flow F1 circulating in a primary gas flow duct, located in a radially internal portion of the turbomachine and in a secondary flow F2 circulating in a secondary gas flow stream, located in a radially outer portion of the turbomachine.

[0032] FIG. 1 represents a block diagram in axial section of a measuring system 200 for a turbomachine in position in a turbomachine 100 with bypass flow comprising from the outside to the inside: an external casing 120, an external duct flow 140 delimited on the outside by the outer casing 120 and partly internally by an internal casing 130, and an internal flow vein 150.

In the embodiment of Figure 1, the measuring system 200 comprises a measuring probe 210, called intrusive, as well as a dynamic sealing device 220 ensuring both the introduction and the guidance of the measurement probe 210 inside the turbomachine 100, as well as the seal between the various compartments of the turbomachine (external environment, external vein 140, internal vein 150) through which the measurement probe 210 passes.

The measurement probe 210 is indifferently any means making it possible to carry out a measurement of a physical quantity (such as for example the pressure, the temperature, the concentration of particles, the speed, etc.) inside a turbomachine , such as for example a thermocouple, an anemoclinometric probe, a light beam (laser, IR, UV, ...).

The measurement probe 210 is associated with information processing means (not shown) measured by said measurement 210.

In the exemplary embodiment shown, the measurement probe 210 makes it possible to measure a physical quantity of an internal flow vein 150 of a turbomachine 100.

The dynamic sealing device 220 according to the invention comprises a first body, for example a sheath 230 having an outer end 231, in the form of a cup, intended to bear against the outer surface 121 of the wall of the housing external 120, and to cover a portion of the external surface 121 around a passage opening 122 passing through the wall of the external casing 120.

The sleeve 230 has a central body 232, for example of substantially tubular shape, and extending substantially radially (with respect to the axis of the turbomachine) in the turbomachine in the external vein 140, as well as an end internal 233 formed by an annular flange extending radially relative to the longitudinal axis of the central body 232 of the sleeve 240.

To seal the outer vein 140 at the passage opening 122 of the wall of the outer casing 120, the outer end 231 of the sheath 230 is advantageously secured to the outer surface 121 of the wall of the outer casing 120.

To seal the external vein 140 at the level of the passage orifice 132 of the wall of the internal casing 130, the internal end 223 of the sleeve 230 cooperates with a second body, for example an integral bush 240 of the internal casing 130, via a sealing means, such as a seal 250, for example an annular segment seal.

To this end, the inner end 233 of the sleeve 232 further has an intermediate flange 234 surrounding the central part 232 of the sleeve 230 and positioned at a certain distance from the inner end flange 233 so as to form an annular housing 235, called a seal groove, configured to receive the seal 250.

[0042] The seal 250 has an internal diameter greater than the diameter of the annular housing 235 so that the seal is axially movable within the annular housing 235.

The distance between the two flanges 233, 234 defining the height of the annular housing 235 is greater than the thickness of the seal 250 so as to allow movement in the radial direction of the seal inside of the annular housing 235 and therefore the radial differential expansions of the various elements of the turbomachine 100, and in particular of the outer casing 120 and of the inner casing 130.

The sleeve 240 has the shape of an inverted cup, or bowl, with an upper cylindrical portion 241 and a lower cylindrical portion 242 having an internal diameter substantially equivalent to the internal diameter of the sleeve 230 for the passage of the measurement probe 210 The upper portion 241 of the socket 240 has an internal diameter greater than the internal diameter of the lower portion 242.

The outer diameter of the lower portion 242 of the sleeve 240 is greater than the diameter of the passage hole 132 formed at the wall of the internal casing 130. The lower portion 242 of the sleeve 240 is intended to come in contact with the radially outer surface 131 of the wall of the inner casing 130 and is configured to ensure a seal between the external vein 140 and the internal vein 150. Advantageously, the lower portion 242 of the sleeve 240 is secured to the radially outer surface 131 of the wall of the internal casing 130, ie on the surface delimiting the external flow vein 140.

The upper portion 241 of the sleeve 240 is configured to receive the inner end 233 of the sleeve 230 as well as the seal 250. The seal 250, of the segmented seal type, is sized to be able to be inserted in the annular groove 235 of the sleeve 230 and to come to match the inside of the cavity formed by the upper portion 241 of the sleeve 240, so that the peripheral periphery of the seal 250 is in direct contact with the internal wall of the cavity of the upper portion 241 of the sleeve 240, and ensures a sealed contact.

The sheath 230 and the sleeve 240 cooperate so as to define a passage 205 inside the external vein 140 for the passage of the measurement probe, and to allow the introduction of the measurement probe to the interior of the internal vein 150 without disturbing the aerothermal conditions in the external vein 140.

The measurement probe 210 can be fixed or mobile. However, the sealing device 220 according to the invention advantageously makes it possible to be able to use a mobile measuring probe while respecting the sealing conditions between the two veins.

For this purpose, the measurement probe can be set in motion by a device controlled manually or even automatically.

The seal 250 serves as a dynamic connection between the sleeve 230 and the sleeve 240 and ensures a dynamic seal between these two elements and therefore between the external vein and the internal vein on which the sleeve 230 and the socket 240 are respectively secured.

The assembly thus configured also makes it possible to make up for the differential expansions inherent in the operation of the turbomachine, and in particular the axial differential expansions between the sleeve 230 (and therefore the outer casing 120 on which it is integral) and the internal casing 130 and the radial differential expansions between the internal casing 130 and the sleeve 230. In addition, the sleeve 240 has a housing 243 formed between the upper portion 241 of the sleeve 240 and the lower portion 242 of the sleeve 240. The housing 243 is oriented so as to open at the level of the radially internal part of the sleeve 240 (ie taking the axis of revolution of the sleeve as the reference axis). The housing 243 is configured to receive and maintain in position a second sealing means 260 housed inside said housing 243 ensuring, in cooperation with the measurement probe 210, a seal on either side of the passage 205 formed by the sheath. 230 and socket 240.

The second sealing means 260 is for example a movable ring-shaped cup housed inside said housing 243.

The movable cup 260 has a passage orifice 261 having a diameter adjusted to the external diameter of the measurement probe 210 intended to pass through the movable cup 260 as illustrated in FIG. 1.

The movable cup 260 allows the internal vein 150 to be isolated from the inside of the sheath 230, the flow of the internal vein 150 being blocked in the lower portion 242 of the sleeve 240. The movable cup 260 also allows to allow the axial displacement of the measuring probe 210 due to the axial expansions, by axial displacement of the movable cup inside the housing 243 of the sleeve

240.

The diameter of the orifice 261 of the movable cup 260 is adjusted to that of the measuring probe 210, to ensure a seal at this level of the cup / probe. Furthermore, the movable cup 260 is trapped in a cavity, the thickness of which is slightly greater than that of the movable cup 260, which cup is, therefore, movable in translation in its housing. Therefore, the measurement probe 210 is radially movable (in the orifice 261 of the movable cup 260) and the probe + cup assembly can move in translation relative to the socket

241, to accommodate the differential expansions that exist between the two housings 120 and 130, whether they are axial or azimuthal (if one "turns" relative to the other, or any combination of its two movements).

The movable cup 260 also makes it possible to authorize the radial displacement of the measurement probe 210 in the turbomachine in order to achieve radial explorations of the internal flow vein. The cup is metallic to withstand the environment both from a thermal and chemical point of view, etc. and is chosen to be compatible with that of the probe, i.e. its hardness is lower than that constituting the probe so as not to damage said probe.

Thus, the technical solution described above makes it possible to achieve two complementary degrees of sealing: a first sealing produced by the movable cup 260 and a second sealing produced by the seal 250 ensuring dynamic sealing between the sheath 230 and socket 240.

As mentioned above, the seal 250 provides dynamic sealing between the external 140 and internal 150 veins while ensuring compensation for the differential expansions (axial and radial) between the housings 120, 130.

The movable cup 260 provides dynamic sealing between the inside of the sheath 230 and the internal vein 150 while allowing the axial displacement of the probe due to the differential expansions, as well as the radial displacement of the measuring probe 210 allowing to modify the radial position in the vein of the measuring probe 210.

Depending on the pressure conditions in the external and internal flow veins, and the pressure differential between the two flow veins, it is also envisaged to provide a ventilation flow through the sheath in order to there guarantee controlled aerothermal conditions compatible with the environment of the probe. Thus if the pressure in the flow 140 is greater than that in the flow 150, it is possible to provide a few orifices of small dimensions in the sleeve 232 through which a small flow of fluid will flow naturally. Thus the cavity 205 will be ventilated, contributing on the one hand to the cooling of the probe 210 and to the ventilation of the dead water zone at the level of the base of the socket, where it is welded to the wall 130 (zone 132) .

Claims

[Claim 1] Dynamic sealing device (220) for a measuring system (200) comprising a measuring probe (210) intended to pass through a first engine compartment (140) of a turbomachine and to measure a physical quantity in a second engine compartment (150), the first engine compartment (140) being delimited in its radially outer portion by an outer casing (120) and in its radially inner portion by an inner casing (130), the second engine compartment (150) being delimited in its radially outer portion by said inner casing (130), said dynamic sealing device (220) being characterized in that it comprises:

- a first body (230) configured to be positioned inside said first engine compartment (140) and secured to the outer casing (120),

- a second body (240) configured to be positioned inside said first engine compartment (140) and secured to the internal casing (130), the first body (230) and the second body (240) defining a passage (205) inside the first engine compartment (130) for the introduction of said measurement probe (210);

- a first sealing means (250) housed in an annular housing (235) provided at said first body (230), said first sealing means (250) ensuring sealed contact with said second body (240);

- a second sealing means (260) formed inside said passage (205) configured to cooperate with said measurement probe (210) and to ensure a seal between the two ends of said passage (205) formed by said first body (230) and said second body (240), said second sealing means (260) is movable axially and radially with respect to the axis of the turbomachine, in said housing (235).

[Claim 2] Dynamic sealing device (220) for a measuring system (200) according to the preceding claim characterized in that the first sealing means (250) is housed in an annular housing (235), said annular housing ( 235) being:

- provided at said first body (230), said first sealing means ensuring sealed contact with said second body (240), or

- Provided at said second body (240), said first sealing means ensuring sealed contact with said first body (230).

[Claim 3] Dynamic sealing device (220) for a measuring system (200) according to the preceding claim characterized in that the annular housing (235) is provided at one end of said first body (230) or at the level from one end of said second body (240).

[Claim 4] Dynamic sealing device (220) for a measuring system (200) according to one of claims 2 to 3 characterized in that the first sealing means (250) is movable axially and radially with respect to the axis of the turbomachine in said annular housing (235).

[Claim 5] Dynamic sealing device (220) for a measuring system (200) according to one of the preceding claims, characterized in that the first sealing means (250) is a segment seal.

[Claim 6] Dynamic sealing device (220) for a measuring system (200) according to one of the preceding claims characterized in that said second sealing means (260) has an orifice (261) for the passage of said measurement probe (210), said orifice (261) having a diameter configured to ensure sealed contact with said measurement probe (210) and to allow relative displacement of said measurement probe (210).

[Claim 7] Dynamic sealing device (220) for a measuring system (200) according to one of the preceding claims characterized in that said second sealing means (260) is housed in a housing (243) provided at said first body (230) or at said second body (240).

[Claim 8] Dynamic sealing device (220) for a measuring system (200) according to the preceding claim characterized in that said second sealing means (260) is movable axially and radially with respect to the axis of the turbomachine , in said housing (243).

[Claim 9] Measuring system (200) for measuring a physical quantity inside an engine compartment of a turbomachine, said measuring system comprising: - a measuring probe (210) intended to pass through a first engine compartment (140) of a turbomachine and measuring a physical quantity in a second engine compartment (150);

- a dynamic sealing device (220) according to one of the preceding claims. [Claim 10] By-pass turbomachine comprising a measuring system (200) according to the preceding claim for measuring a physical quantity inside a primary flow stream of a primary flow by means of a measuring probe (210) passing through a secondary stream flow vein.