FR3108653A1 - DYNAMIC SEALING DEVICE FOR TURBOMACHINE PROBE - Google Patents

Abstract

The invention relates to a dynamic sealing device (220) for a measurement system (200) comprising a measurement 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) delimiting a passage (205) to the interior of the first engine compartment (130) for the introduction of said 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) made inside said passage (205) configured to cooperate with said measuring probe (210) and to ensure a seal between the two ends of said passage (205) made by said first body ( 230) and said second body (240). Abstract Figure: Figure 1.

Description

DYNAMIC SEAL DEVICE FOR TURBOMACHINE PROBE

TECHNICAL FIELD OF THE INVENTION

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 flux flows within a turbomachine.

The invention relates more particularly to a dynamic sealing device allowing the introduction as well as the movement of a measurement probe in a flow path of a turbomachine, and capable of ensuring a seal between different aerothermal conditions of a turbomachine. .

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

TECHNICAL BACKGROUND

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, it is however necessary to carry out, in addition, so-called “resetting” operations of these digital codes and software with measurements on test turbomachines in order to improve their predictive character. Such resetting operations allow substantial savings of time and money in the initial phases of turbomachinery development.

These "adjustments" can only be envisaged by means of unsteady data collected within the turbomachine itself, in order to take into account all the aerodynamic/thermal/mechanical coupling phenomena of which the turbomachine is the seat, such as the high pressure turbine in particular. .

• l’environnement aérothermique de la sonde ; notamment par les niveaux de pression et de température élevés au sein de l’écoulement en question ;
• le confinement associé à la compacité de plus en plus importante des turbomachines ;
• la traversée de parois étanches multiples délimitant différents environnements aérothermiques avec des pressions, des températures et des concentrations différentes ;
• la nécessité de réaliser une étanchéité efficace au niveau de chaque interface de la turbomachine délimitant des conditions aérothermiques souvent très différentes (par exemple entre une veine interne et une veine externe d’une turbomachine à double flux) pour ne pas dégrader son fonctionnement ;
• la maitrise des dilatations différentielles radiales et axiales des différentes pièces qui peuvent être importantes, lors des phases opérationnelles, et en particulier durant les transitoires thermiques.

However, the measurement of any quantity (for example 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 containment associated with the increasingly compactness of turbomachines;
• the crossing of multiple sealed 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 inner stream and an outer stream 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.

In this context, the invention aims to propose a dynamic sealing device configured to allow the introduction of a measurement probe into a flow of a turbomachine, while preserving the integrity of the various internal flows of the turbomachine, despite very different aerothermal conditions at the interfaces, compatible with the geometric constraints of current compact turbomachines, allowing radial displacement of the measurement probe and allowing differential expansion between stator-stator or even stator-rotor to be absorbed.

• un premier corps configuré pour être positionné à l’intérieur dudit premier compartiment moteur et solidarisé au carter externe,
• un deuxième corps configuré pour être positionné à l’intérieur dudit premier compartiment moteur et solidarisé au carter interne, le premier corps et le deuxième corps délimitant un passage à l’intérieur du premier compartiment moteur pour l’introduction de ladite sonde de mesure ;
• un premier moyen d’étanchéité configuré pour assurer une liaison mobile et étanche entre le premier corps et le deuxième corps ;
• un deuxième moyen d’étanchéité ménagé à l’intérieur dudit passage configuré pour coopérer avec ladite sonde de mesure et pour assurer une étanchéité entre les deux extrémités dudit passage ménagé par ledit premier corps et ledit deuxième corps.

To this end, the invention relates to a dynamic sealing device for a measurement system comprising a measurement 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 arranged inside said passage configured to cooperate with said measurement probe and to provide sealing between the two ends of said passage arranged by said first body and said second body.

In the present application, a probe will designate 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.) whether it is intrusive such as a thermocouple or an anemoclinometric probe, or even non-intrusive, such as a light beam (laser, IR, UV, etc.). In both cases, the means of measurement, subsequently referred to by the general term "probe", travels inside a tube formed by a sheath opening into a flow path. The probe can be fixed or mobile, that is to say set in motion by a manually or automatically controlled device.

The term "dynamic sealing device" means a sealing device allowing the radial displacement (relative to the engine axis of a turbomachine) of a probe and allowing the radial and axial expansion inherent in the operating conditions of a turbomachinery.

The invention advantageously makes it possible to achieve a seal between two compartments of a turbomachine exhibiting high and different temperature and pressure conditions, while allowing differential expansion of the parts of the turbomachine and allowing movement of the so as to allow radial exploration of a flow channel 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 engine nozzle. exhaust.

• une étanchéité dans des conditions sévères de pression et de température relatives au fonctionnement d’une turbomachine ;
• un rattrapage des dilatations différentielles axiales et/ou radiales des carters les uns par rapport aux autres ;
• le déplacement radial de la sonde de manière à permettre différentes positions radiales de la sonde de mesure pour une exploration radiale d’une veine d’écoulement de turbomachine.

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;
• a catch-up of the differential axial and/or radial expansions of the casings with respect to each other;
• the radial displacement of the probe so as to allow different radial positions of the measurement probe for radial exploration of a turbomachine flow path.

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 all technically possible combinations.

Advantageously, the first sealing means is housed in an annular housing made at the level of said first body, said first sealing means providing sealed contact with said second body.

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

Advantageously, the annular housing is formed 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 the level of the said first body or at the level of the said second body.

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

• une sonde de mesure destinée à traverser un premier compartiment moteur d’une turbomachine et à mesurer une grandeur physique dans un deuxième compartiment moteur ;
• un dispositif d’étanchéité dynamique selon l’invention.

The invention also relates to a measurement system for measuring a physical quantity inside an engine compartment of a turbomachine, said measurement system comprising:

• a measurement probe intended to pass through a first engine compartment of a turbomachine and to measure a physical quantity in a second engine compartment;
• a dynamic sealing device according to the invention.

The invention also relates to a dual-flow turbomachine comprising a measurement system according to the invention for measuring a physical quantity inside a primary stream of flow of a primary stream by means of a measurement probe passing through a secondary stream of sidestream flow.

The invention and its various applications will be better understood on reading the description which follows and on examining the figure which accompanies it.

BRIEF DESCRIPTION OF FIGURES

is a block diagram illustrating the dynamic sealing device according to the invention traversed by a measurement probe.

Figure 1 is shown for information and example only and is not therefore in any way limiting of the invention.

DETAILED DESCRIPTION

In the present application, the terms “upstream” and “downstream” are defined with respect to the normal flow direction of the gas (from upstream to downstream) through a turbomachine.

The "turbomachine axis" or "engine axis" is also called the axis of rotation of a turbomachine rotor. 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. Similarly, 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", "external", "external" 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 dual-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 vein, located in a radially internal portion of the turbomachine and into a secondary flow F2 circulating in a secondary gas flow stream, located in a radially outer portion of the turbomachine.

FIG. 1 represents a block diagram in axial section of a measurement system 200 for a turbomachine in position in a dual-flow turbomachine 100 comprising, from the outside inwards: an external casing 120, an external flow path 140 delimited in the external part by the external casing 120 and in the internal part by an internal casing 130, and an internal flow vein 150.

In the exemplary embodiment of FIG. 1, the measurement system 200 comprises a so-called intrusive measurement probe 210, as well as a dynamic sealing device 220 ensuring both the introduction and the guiding of the measurement 210 inside the turbine engine 100, as well as the seal between the different compartments of the turbine engine (external environment, external stream 140, internal stream 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 by example a thermocouple, an anemoclinometric probe, a light beam (laser, IR, UV, etc.).

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

In the exemplary embodiment represented, the measurement probe 210 makes it possible to measure a physical quantity of an internal flow stream 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 come into abutment with the outer surface 121 of the wall of the outer casing 120, and to cover a portion of the outer surface 121 around a passage orifice 122 passing through the wall of the outer casing 120.

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

To ensure the tightness of the external vein 140 at the level of the passage orifice 122 of the wall of the external casing 120, the external end 231 of the sheath 230 is advantageously secured to the external surface 121 of the wall of the external casing 120 .

To ensure the tightness of 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 sheath 230 cooperates with a second body, for example a sleeve 240 secured to the internal casing 130, via a sealing means, such as a seal 250, for example an annular segment seal.

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

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

The distance between the two flanges 233, 234 delimiting 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 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 a cylindrical upper portion 241 and a cylindrical lower portion 242 having an internal diameter substantially equivalent to the internal diameter of the sheath 230 for the passage of the measurement probe 210. upper 241 of the sleeve 240 has an inside diameter greater than the inside 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 orifice 132 provided at the level of the wall of the internal casing 130. The lower portion 242 of the sleeve 240 is intended to come into contact with the radially outer surface 131 of the wall of the inner casing 130 and is configured to provide a seal between the outer vein 140 and the inner 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, i.e. on the surface delimiting the external stream 140 of flow.

The upper portion 241 of the sleeve 240 is configured to receive the inner end 233 of the sheath 230 as well as the seal 250. The seal 250, of the segmented seal type, is sized to be able to be inserted into the groove annular 235 of the sheath 230 and to come to marry the interior 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 delimit a passage 205 inside the external vein 140 for the passage of the measurement probe, and to allow the introduction of the measurement probe inside 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 measuring 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 makes it possible to ensure a dynamic seal between these two elements and therefore between the external vein and the internal vein on which the sleeve 230 and the sleeve 240 are respectively united.

The assembly thus configured also makes it possible to compensate 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 expansions radial differentials between the inner casing 130 and the sheath 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 out at the level of the radially internal part of the sleeve 240 (i.e. taking as reference axis the axis of revolution of the sleeve). The housing 243 is configured to receive and hold 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 provided by the sheath. 230 and the socket 240.

The second sealing means 260 is for example a mobile cup of annular shape housed inside said housing 243.

The mobile 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 mobile cup 260 as illustrated in FIG. 1.

The mobile cup 260 makes it possible to isolate the internal vein 150 from the interior of the sheath 230, the flow of the internal vein 150 being blocked in the lower portion 242 of the sleeve 240. The mobile cup 260 also makes it possible to authorize the axial displacement of the measuring probe 210 due to the axial expansions, by axial displacement of the mobile cup inside the housing 243 of the sleeve 240.

The diameter of the orifice 261 of the mobile cup 260 is adjusted to that of the measuring probe 210, to ensure sealing at this cup/probe level. Furthermore, the mobile cup 260 is imprisoned in a cavity, the thickness of which is slightly greater than that of the mobile cup 260, which cup is, therefore, mobile in translation in its housing. As a result, the measuring probe 210 is radially mobile (in the orifice 261 of the mobile cup 260) and the probe + cup assembly can move in translation relative to the sleeve 241, to accommodate the differential expansions that exist. between the two housings 120 and 130, whether axial or azimuth (if one "rotates" relative to the other, or any combination of its two movements).

The mobile cup 260 also makes it possible to authorize the radial displacement of the measuring probe 210 in the turbomachine in order to carry out radial explorations of the internal flow stream. 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 the said probe.

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

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

The mobile cup 260 provides a dynamic seal between the interior 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 making it possible to modify the radial position in the vein of the measuring probe 210.

Depending on the pressure conditions in the external and internal flow paths, and the pressure differential between the two flow paths, it is also envisaged to provide a ventilation flow through the sheath in order to guarantee conditions there. controlled aerothermal temperatures compatible with the environment of the probe. Thus, if the pressure in the stream 140 is greater than that in the stream 150, it is possible to provide a few small-sized orifices in the sheath 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 foot of the sleeve, where it is welded to the wall 130 (zone 132) .

Claims (10)

Dynamic sealing device (220) for a measurement system (200) comprising a measurement 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 external via said internal 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) delimiting a passage (205) to inside the first engine compartment (130) for the introduction of said measuring probe (210);
• a first sealing means (250) configured to ensure a movable and sealed connection between the first body (230) and the second body (240);
• a second sealing means (260) made inside said passage (205) configured to cooperate with said measuring probe (210) and to ensure a seal between the two ends of said passage (205) made by said first body ( 230) and said second body (240).

Dynamic sealing device (220) for 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:

• formed at said first body (230), said first sealing means providing sealing contact with said second body (240), or
• provided at said second body (240), said first sealing means providing sealing contact with said first body (230).

Dynamic sealing device (220) for 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 one end said second body (240). Dynamic sealing device (220) for 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). Dynamic sealing device (220) for measuring system (200) according to one of the preceding claims, characterized in that the first sealing means (250) is a segment seal. Dynamic sealing device (220) for 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 measuring probe ( 210), said orifice (261) having a diameter configured to ensure sealing contact with said measurement probe (210) and to allow relative movement of said measurement probe (210). Dynamic sealing device (220) for measuring system (200) according to one of the preceding claims, characterized in that the said second sealing means (260) is housed in a housing (243) provided at the level of the said first body ( 230) or at said second body (240). Dynamic sealing device (220) for measuring system (200) according to the preceding claim, characterized in that the said second sealing means (260) is movable axially and radially with respect to the axis of the turbomachine, in the said housing (243). Measurement system (200) for measuring a physical quantity inside an engine compartment of a turbomachine, said measurement system comprising:

• a measurement 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);
• a dynamic sealing device (220) according to one of the preceding claims.

Dual-flow 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 vein of secondary flow flow.