阅读说明：本技术 用于冷却涡轮机壳体的设备 (Apparatus for cooling a turbine casing ) 是由 杰克斯·马赛尔·亚瑟·布纳尔 艾蒂安·杰哈尔德·约瑟夫·卡内尔 埃默里克·克里斯蒂安·阿莫里·德 于 2019-06-25 设计创作，主要内容包括：本发明公开了用于冷却涡轮机壳体的设备和涡轮机。本发明通过固定到表皮(2)上的环(4)而不是通过与环相距一距离的圆形斜面来执行壳体(2)的热收缩以尽可能好地调节转子和定子之间的内部间隙。环(4)包括在收集箱(8)与表皮(2)之间的多孔板(7),该多孔板被放置在箱(8)的开口上、平行于表皮(2)并呈较短距离,以施加不变的和已知的通风条件。(The invention discloses an apparatus for cooling a turbine housing and a turbine. The invention performs the thermal contraction of the casing (2) by means of a ring (4) fixed to the skin (2) instead of by means of a circular bevel at a distance from the ring to adjust the internal clearance between rotor and stator as good as possible. The ring (4) comprises a perforated plate (7) between the collection box (8) and the epidermis (2), which is placed on the opening of the box (8), parallel to the epidermis (2) and at a short distance, to impose constant and known ventilation conditions.)

1. Apparatus for cooling a rotating casing of a turbine by means of an air flow, the apparatus comprising: a plate (7) of circular band surrounding the casing, said plate having edges (10, 11) fixed to the casing (1) and a main perforated portion (9) parallel to the casing (7), said plate and the casing (1) delimiting an air blowing chamber (12) provided with a discharge opening (15); a collecting box (8) surrounding the plate and defining, with the plate (7), a gas distribution chamber (18) while covering a major portion of the plate; a cooling gas supply container (5) at a distance from the collection tank; and at least one connection duct (6) connecting the container to the tank, characterized in that the device comprises a projection (13, 14) projecting on the casing to act as a support for the edges (10, 11) of the plate (7), and in that the projection (13, 14) produces a stop for a first (10) of the edges of the plate in the axial direction (X) of the casing and a support for a second (11) of the edges of the plate (7) in the radial direction (R) of the casing.

2. Device according to the preceding claim, characterized in that the edges of the plates are substantially perpendicular to each other.

3. The apparatus according to claim 1, characterized in that the edges (16, 17) of the collecting box (8) are parallel to the edges (10, 11) of the plate, respectively, on which the edges of the collecting box are placed and fixed.

4. Device according to claim 3, characterized in that at least one of the protrusions (14) is provided with a discharge opening (15).

5. The apparatus according to claim 1, characterized in that the connecting duct (6) is curved and slides through the wall of the collection tank or through the wall of the container or through both walls.

6. A turbine, characterized in that it comprises a device according to claim 1.

7. The turbomachine of claim 6, wherein the plate is positioned around a portion of the housing where the circular ribs are provided.

8. Turbomachine according to claim 6, characterised in that the cooling device comprises a plurality of plates and collecting boxes respectively associated with the plates, the plates and boxes forming successive rings (4) around the casing in the axial direction thereof.

Technical Field

The subject of the invention is a device for cooling a turbine casing by means of a gas flow.

Background

A widely used method for adjusting the clearance between the fixed and moving blades on the one hand and the rotor and stator on the other hand in turbomachines comprises blowing a cold air flow onto the casing of the stator to cause thermal contraction of the diameter of the casing. This flow is typically a small fraction of the turbine flow tube flow extracted from the compressor where the gas is at high pressure and still cold, left to circulate in a duct extending along the flow tube, and blown onto the hotter turbine of the machine. The device usually comprises an annular ramp surrounding the housing of the stator at a distance from the housing of the stator and provided with blow holes directed towards the housing. Document US 6149074 describes such a cooling device.

A disadvantage of this device is the lack of precision. The position of the bevel cannot always be kept optimal due to deformations, in particular due to differential thermal expansions due to different heats to which the machine is subjected during operation and to manufacturing tolerances of the blowing device comprising the bevel. In particular, since the housing is generally conical, these deformations and differential expansions may displace the ramp not only in the axial direction of the housing but also in the radial direction of the housing. Thus, the ramp can be located beside the point of the casing that should be subjected to the blow (usually the most rigid part that surrounds the circular ribs that reinforce it and is correctly dimensioned) and the distance of the ramp from the casing can also be detuned, or even disappear in some cases. However, very high positioning accuracy is required to obtain good quality clearance adjustment in modern engines, and positioning errors or displacements in the order of millimeters can compromise blow quality. Furthermore, if the shell comes into contact with the ramp, the ramp will burst if the shell expands more.

If the ramp is connected to the housing by means of a connecting device instead of being completely separated from the housing as in the above-mentioned patent, the disadvantages of positioning errors when mounting the device on the housing or during operation can be reduced, but deformations and differential thermal expansion can cause very great restrictions on the assembly and also possibly cracks.

Therefore, today it cannot be solved in a satisfactory manner to keep the ramp cool by blowing air at a well-defined position, not only axial but also radial, relative to the housing subjected to the blowing air.

The subject of document EP 2236772 a2 is a device in which the ramp is assembled to the housing. The inclined plane is composed of an inner plate provided with blowholes, an outer plate defining a blowroom together with the inner plate, and an intermediate plate capable of making the air flow to the blowholes uniformly. The plates are provided with overlapping edges and are screwed to retaining lugs on the housing. This structure is relatively complex and presents positioning defects, which are very important in fields where very high precision is required, and risks can arise without specific installation precautions.

Disclosure of Invention

The invention is designed to eliminate this imprecise disadvantage of cooling. In general form, the invention relates to an apparatus for cooling a rotating casing of a turbomachine by means of a gas flow, the apparatus comprising: a plate of circular strip surrounding the casing, the plate having an edge fixed to the casing and a main perforated portion parallel to the casing, the plate and the casing defining an air blowing chamber equipped with a discharge opening; a collection box surrounding the plate and defining with the plate a gas distribution chamber while covering a major portion of the plate; a gas supply vessel at a distance from the tank; and at least one connecting conduit connecting the container to the tank; and the apparatus is characterized in that the position of the plate on the housing is ensured by a projection projecting from the housing to serve as a support or stop for the edge of the plate; and the projection produces a stop against a first one of the edges of the plate in the axial direction of the housing and a support against a second one of the edges of the plate in the radial direction of the housing.

The invention is therefore based mainly on the connection of the housing to the end of a blowing device (i.e. a plate through which the gas is blown out) which is parallel to the housing and which is kept at a constant and well-defined distance from the housing due to the two stop supports obtained in perpendicular directions. The geometric blowing conditions are thus maintained uniform irrespective of the operating variations of the machine and the deformations to which the different parts are subjected, which do not affect such a more or less non-deformable connection of the housing and the end of the blowing device.

The protruding protrusion on the housing may be provided with a vent.

In a preferred alternative embodiment, the collection box comprises edges respectively parallel to and placed on the edges of the plates; in particular, if the panel comprises a first substantially flat edge and a second edge substantially perpendicular to the first edge, this arrangement makes it possible to easily assemble the collecting chamber to the panel.

According to a preferred arrangement, the connector is curved and slides through the wall of the tank, the wall of the tank or the wall of the tank, which makes it possible to compensate for differential expansions in the direction of the sliding movement or possibly in any direction.

Another aspect of the invention is a turbine comprising such a cooling device, the plate then advantageously being able to be positioned around the portion of the casing provided with the circular ribs. The cooling device may further comprise a plurality of plates and collecting boxes respectively associated with the plates, the plates and boxes forming successive rings around the housing in the axial direction of the housing.

Drawings

The various aspects, features and advantages of the present invention will now be described in detail with reference to the following drawings, which illustrate preferred embodiments of the invention and are given for illustrative purposes only:

figure 1 is an overall view of the apparatus in a longitudinal section of the machine;

figure 2 is an enlarged view of a unit of the apparatus;

figure 3 shows a perforated plate;

figure 4 shows a housing;

figure 5 shows a collection tank;

and figure 6 shows the blowing gas flow.

Detailed Description

Fig. 1 gives a general view of the device and its environment. The turbine comprises a housing 1 surrounding an axial direction X. The shell 1 comprises a conical skin 2, typically reinforced by circular ribs 3, and the skin 2 thus defines a more rigid annular portion of the shell 1. The cooling device comprises a ring 4 around the casing 1, which ring bears against a circular band of the skin 2 and is preferably mounted in front of the ribs 3. The ring 4 is connected by means of a connector 6 having a curved shape to a cold gas container, here an air supply tank 5, which extends to a distance from the ring.

Figure 2 shows one of the rings 4 of the device in detail. The ring 4 comprises a plate 7 with a ring and conical shape integral in the axial direction X (possibly consisting of angular sectors assembled together) and a collection box 8 covering the plate 7, which is placed on the skin 2 while being fitted around the skin 2. Fig. 3 shows a plate 7 comprising a main perforated portion 9 (crossed by a plurality of perforations) and two transverse edges 10 and 11. The taper of the plate 7 is the same as the taper of the part of the epidermis 2 over which the plate 7 extends, so that the main part 9 is parallel to the epidermis 2 and separated from the epidermis 2 by a blow chamber 12 having a constant depth of a few millimetres (for example 2 millimetres). It is assumed that this depth remains constant and uniform throughout the entire extent of the insufflation chamber 12 in order to maintain rigidity during assembly and operation. The first transverse edge 10 is substantially flat and extends parallel to the axial direction X, while the second transverse edge 11 (at the larger diameter of the plate 7) is substantially cylindrical. The skin 2 (fig. 4) is provided with two rigid protrusions 13 and 14, which are annular and protrude in the form of ribs for receiving the lateral edges 10 and 11, respectively, to establish a supporting or stop condition. The first transverse edge 10 abuts against a transverse face of the projection 13, which is flat and oriented in the axial direction X, while the second transverse edge 11 is pressed against an outer face of the other projection 14, which is cylindrical and has the same diameter as the second transverse edge and is oriented in the radial direction R. The projections 14 are provided with discharge grooves 15 regularly distributed on the circumference of the projections 14 to enable the air to be discharged from the blowing chamber 12. The collecting bin 8 also has an annular shape and comprises (fig. 5) a first flat transverse edge 16 perpendicular to the axial direction X and an opposite second transverse edge 17 oriented along the axial direction X and cylindrical or slightly conical. The transverse edges 16 and 17 have the same orientation as the transverse edges 10 and 11 of the plate 7, respectively, and the transverse edges 16 and 17 may be placed over the transverse edges 10 and 11 and fixed to the transverse edges 10 and 11 by soldering, welding or other means. The transverse edges 10 and 11 of the plate 7 are similarly brazed, welded or otherwise secured to the projections 13 and 14. The support or stop in a substantially perpendicular direction between the edges 10 and 11 of the panel 7 on the one hand and the tabs 13 and 14 or the edges 16 and 17 of the collecting box on the other hand provides a simple assembly to be established and which has little mechanical constraints. Furthermore, the collecting tank 8 is formed by a continuous plate between the transverse edges 16 and 17, which is bent outwards in the radial direction R and which opens only on the inner radial side, at the point where the collecting tank 8 covers the main portion 9 of the plate 7. The plate 7 thus separates the blowing chamber 12 from a distribution chamber 18, which is located radially outside the blowing chamber and is delimited by the collection chamber 8.

However, the wall of the collecting chamber 8 is perforated at the point of the connector 6. The connector passes through the wall of the collection tank and is connected to the supply tank 5 via an axial branch 19, while passing through the wall of the supply tank via another inclined branch 20, which is separated from the previous branch by a bend 21. Advantageously, the ends of the branches 19 and 20 penetrate into the collection tank 8 and the supply tank 5 by means of joints that allow the branches 19 and 20 to slide through the walls of the collection tank and the supply tank, so as to adapt the apparatus to variations in position, for example due to thermal expansions in the machine, in particular between the casing 1 and the supply tank 5.

A single connector 6 between the supply tank 5 and each ring 4 has been shown. A plurality of connectors 6 may be provided for each ring 4, distributed around the circumference of the ring 4. It is then proposed to divide the interior of the collecting chamber 8 into compartments by means of spacers to ensure equal flow in the interior of the collecting chamber. The supply tank 5, common to all the connectors 6, is connected to the compressor of the machine, or possibly to another compressed air source, by a pipe 22, only depicted here.

In operation (fig. 6), compressed air drawn from the compressor reaches the supply tank 5 via the pipe 22, is then distributed into the collection tank 8 by the connector 6 and propagates in the angular direction in the distribution chamber 18 of the collection tank, then passes through the plate 7 by means of the perforations of the plate 7 to enter the puffer chamber and to impinge on the skin 2 at the point of the stiffeners 3, before being discharged to the outside through the slots 15. The uniform depth of the puffer chamber 12 ensures that the air flow beats every part of the epidermis 2 in a constant manner, which makes it possible to anticipate the heat shrinkage applied with high precision. The value of the flow rate can be adjusted, typically by means of a valve placed for example on the tube 22.