RU2443869C2 - Gas turbine rotor cooling device - Google Patents

Abstract

FIELD: machine building.

SUBSTANCE: gas turbine rotor cooling device includes pneumatic drives, cooler, cooled rotating blades with independent cooling systems of entry edge and feather of blade, which are connected to channels in the shank, annular swirling pneumatic device, labyrinth seals and annular cavities. One of annular cavities is formed with stator and rotor part between compressor and turbine and the other one is formed with covering disc and disc of impeller. Flow-through part after compressor is connected by means of pneumatic drive to pneumatic inlet of cooler. Pneumatic outlet of cooler is connected to annular cavity above rotor between compressor and turbine, which has labyrinth seal with increased gap in the area of turbine, behind which a row of holes is located in the covering disc. Holes are connected with the inlet to extension-type tubular pneumatic drives the outlet of each of which is connected to inlet connection pipe of the channel of cooling system of entry edge of cooled turbine rotating blade. Pneumatic outlet of cooler is connected to annular swirling pneumatic device opposite the outlet of which there located in the covering disc is a row of holes with outlet to annular cavity which is connected to longitudinal channels of cooling system of turbine rotating blade feather, which are located in shanks of blades.

EFFECT: cost-effective cooling of rotor of high-temperature gas turbine.

9 cl, 5 dwg

Description

The invention relates to the field of gas turbine engineering and can be used for cooling rotors and impellers with cooled blades, mainly high-temperature gas turbines.

Known technical solution according to US patent 3635586, F01D 5/08, publ. 01/18/1972, where a device for cooling the impeller of a gas turbine provides its cooling with two streams of cooling air. The perforated inlet edge of the working blade 20 of the high-temperature turbine is cooled by air coming from the compressor through the annular screw pneumatic device 52 and then, as an option, through the radial holes 70 in the disk 18 of the impeller or through the slotted grooves 40 between the disk 18 and the ring ring 30, and then through the radial channels in the shank of the blade into the internal cavity of the cooling system 26 of the inlet edge of the cooling blade 20. The feather of the blade 20 and its outlet edge are cooled by the same air due to and the compressor, but already through the autonomous channels 28 in the shank of the blade 20. Air supply due to the compressor to these channels is carried out from the annular cavity 44 in front of the impeller, where it enters through the pneumatic pipe 58 in the stator. The rotor and the impeller disk 18 are cooled by air not participating in the cooling of the impeller 20.

This technical solution has several disadvantages.

It is economically inefficient to cool the rotor, impeller of the turbine and the blades with separate streams of cooling air, which leads to its increased consumption.

The presence in the peripheral part of the disk of mounting holes and holes of the cooling system degrades the strength characteristics of the impeller.

To eliminate leaks of cooling air of high pressure, brought into the gap between the disk and the end of the shank of the blade, it is necessary to introduce additional design measures to seal the Christmas tree lock. Known structural solutions for sealing a Christmas tree lock are not effective.

It is also known a device for cooling the impeller of a gas turbine containing a cover segment disk 1 with radial tides 16, in which channels 17 are made with air supplied into them due to the compressor. This air is then supplied through the shaped pipe 18 to the air inlet channels 9 to the cooled blade 5. In addition, in the shank 13 of the cover disk 1 there are grooves 25 through which air from the intermediate stage of the compressor enters the cavity between the cover disk 1 and the disk 2 of the impeller . From this cavity, air enters the gaps 7 of the Christmas-tree lock connection 6 of the blades 5 and the disk 2 of the turbine (see RF Patent 2183747, F01D 5/08, published on 06/20/2002).

The disadvantage of this device is the uneconomical use of cooling air due to the compressor entering through the air line of the radial tide of the cover disk and the profiled pipe into the cooling systems of the inlet edge and feather of the cooled blade. For cooling blades with a perforated inlet edge, the connection of the cooling system of its inlet edge and the cooling system of the blade feather is not an optimal solution.

In the considered prototype there is also no reliable, with sufficient tightness, connection of the profiled pipe and the cooled blade.

Known technical solutions are non-optimal and ineffective in terms of using cooling air in the engine cooling system. Here, air that has passed through the labyrinth seal is subsequently discharged into the turbine path and is not used in the blade cooling system.

An expensive technology is the manufacture of segments of a cover disc with pneumatic piping in radial tides.

The claimed invention is aimed at solving the problem of optimal and cost-effective use of the coolant of the working fluid in the cooling system of the rotor of a turbocompressor and the impeller of high-temperature turbines and also ensuring reliable and efficient distribution of cooling air, certain parameters, in the cooling system of a high-temperature gas turbine engine.

These problems are solved in a device for cooling a rotor and an impeller of a gas turbine, containing pneumatic pipelines, a refrigerator, cooled working blades with autonomous cooling systems of the inlet edge and feather of the blade connected to channels in the shank, an annular screw pneumatic device, labyrinth seals and annular cavities, one of which is formed by the stator and the rotor part between the compressor and the turbine, and the other is the cover disk and the impeller disk, and in accordance with the invention the full-time part of the engine behind the compressor via a pneumatic conduit is connected to the pneumatic inlet of the refrigerator, the pneumatic outlet of which is connected to the annular supra-rotor cavity between the compressor and the turbine, which in the turbine region has a labyrinth seal with an increased clearance, behind which there are a number of holes in the cover disk that are connected to the input telescopic tubular pneumatic pipelines, the output of each of which is connected to the inlet pipe of the channel of the cooling system of the inlet edge of the cooled turbine blade s. The number of openings of the casing disk corresponds to the number of telescopic tubular pneumatic pipelines and, accordingly, to the number of cooled blades on the impeller of the turbine. In addition, the pneumatic outlet of the refrigerator is connected to an annular swirling device, opposite to the outlet from which there are a number of holes in the cover disk with an outlet into the annular cavity, which is connected to the channels of the cooling system of the turbine blade of the turbine pen located in the shanks of the blades. Then, behind the last working blade of the compressor, under the rectifier, there is a labyrinth seal, immediately behind which there is an outlet of the pneumatic line connected to the pneumatic outlet of the refrigerator.

The cover disk in the peripheral part has radial cuts and on the periphery in the axial direction rests on the protrusion of the cooled working blades of the gas turbine. In this case, the radial cuts in the cover disk are closed on a series of holes into which air is supplied from the annular swirling device.

And yet, the pneumatic pipe connecting a series of holes in the cover disk to the pipe of the cooling channel of the inlet edge of the turbine blade, consists of a radially arranged composite pipe in which the peripheral pipe is connected to the shaped pipe of the blade with a cone-sphere fit, and telescopically with the lower pipe, that the peripheral pipe has the ability to freely move along its axis, perpendicular to the axis of the engine, by the amount of entry into the cone-sphere connection.

And the shaped pipe of the cooling system of the inlet edge of the cooled blade is made of a L-shaped.

The implementation in the cooling device of the rotor of a gas turbine in the claimed manner, the cooling system according to the thermal circuit with air extraction due to the compressor, its subsequent cooling in the refrigerator and distribution of already cold air according to the parallel-series cooling scheme: in parallel with one part of the cooling air of the lock and pen of the turbine blade and the second part of the rotor of the gas turbine with the sequential operation of this second part of the cooling air in the cooling system of the rotor parts between the compressor and the turbine, and ATEM cooling system perforated rotor blade inlet edges of the high temperature turbine, allows efficient cooling of a large number of high-temperature turbine rotor elements of a limited amount of air, thereby providing a potential economic operation of the turbine rotor cooling system.

At the same time, the location of the cooling air intake holes of the cooling system of the perforated inlet edge of the working blade on the cover disk behind the labyrinth seal allows you to utilize the calculated air leaks through this seal, thereby reducing the total cooling air flow in the engine cooling system.

The use of a composite tubular pneumatic pipeline with a telescopic connection and blades with a profiled L-shaped nozzle ensures ease of assembly-disassembly of the impeller, and, together with the execution of the ends of the peripheral pipeline and a profile nozzle for the cone-sphere connection, reliable tightness of the connection of the high pressure pneumatic pipeline to the cooling system working blades, which increases the resource of the turbine.

The invention is illustrated by drawings, which depict:

figure 1 is a longitudinal section of a gas turbine engine with a thermal diagram of a cooling system of a rotor of a gas turbine;

figure 2 - element a in figure 1;

figure 3 - element B in figure 2 with the pipeline in the open position;

figure 4 - element B in figure 2 with the pipeline in the closed position;

figure 5 - element B in figure 2 with a view of the Christmas tree castle.

A device for cooling the rotor of a gas turbine contains a cooled working blade 1 (figure 5) with two autonomous cooling systems. The first cooling system 2 of the inlet edge 3 has an internal cavity 4 connected to the L-shaped pipe 5, the end of which has a tapered seating surface 6. The inlet edge 3 of the blade 1 has openings 7. The second independent cooling system 8 of the feather of the blade 1 has an internal cavity 9 connected to the holes 10 in the output edge 11 and the radial channels 12 in the shank 13, which also has a trim 14, locking hook 15 (figure 3) and Christmas tree lock 16 for connecting the blades 1 with the peripheral part (rim) 17 of the disk 18 of the rotor 19 (figure 1) gas t the rib 20. The rim 17 has a hook 21 (Fig. 5), into which the latch 22 is inserted. The connection of the blade 1 and the disk 18 in the area of the Christmas tree lock 16 has gaps 23. In addition, the working blade 1 has a step 24 with scallops of the labyrinth seal 25, in which abuts the peripheral part 26 of the cover disc 27, which has rows of holes 28, 29, 30 (FIG. 2), ledges with combs of labyrinth seals 31, 32, peripheral radial cuts 33 (FIG. 4), guiding protrusions 34 (FIG. 5 ) and shank 35 (figure 2). Between the disk 18 and the cover disk 27 there is an annular cavity 36 in which are located tubular pneumatic pipelines (pipelines) 37, 38, interconnected by a movable telescopic connection 39 (Fig.4). At the end of the peripheral pipe 38 there is a sphere 40 (Fig. 3).

In addition, the rotor 19 of the turbine 20 is connected to the rotor 41 (Fig. 1) of the compressor 42. There are a compressor stator 43 with rectifier devices 44, 45 and a diffuser 46. In the rectifier apparatus 45 and in the inner case 47 of the diffuser (stator) 46 there are bypass pneumatic lines 48 and 49, respectively. An annular cavity 53 is formed between the stator 43 and the rotor part 50 connecting the rotor 41 of the compressor 42 and the rotor 19 of the turbine 20 between the existing labyrinth type seals 51. Moreover, the labyrinth seal 51 is located directly behind the working blade of the last stage of the compressor 42, and the labyrinth seal 52 (figure 2) with an increased clearance for guaranteed admission of the estimated amount of air.

There are fasteners 54, an annular swirling pneumatic device 55, pneumatic piping 56 (FIG. 1), 57 and a refrigerator 58 with pneumatic inlet 59 and outlet 60. The direction of movement of the main flows of cooling air is shown. Gaps 61 (figure 2), 62 (figure 3), 63 (figure 4) are indicated.

An annular cavity 36 is formed between the cover disk 27 and the disk 18 of the rotor 19. Here, in the annular cavity 36 are pipelines 37 fixed to the cover disk 27. The pipelines 37 are arranged radially, with one end connected to the holes 29 and the other with the pipe 38. Moreover, the connection of the pipelines 37 and 38 telescopic to each other. Alternatively, the figures show the connection where the upper pipe 38 is inserted into the pipe 37. The telescopic connection 39 allows the pipe 38 to move freely radially. The restriction of the movement of the pipe 38 in the radial direction, from above, is the pipe 5 of the working blade 1. The pipe 38 is joined with the pipe 5 from the pipe 38 along the sphere 40 and from the blade 1 along the cone 6. Axial dimension of the telescopic connection 39 (in the radial direction of the turbine) provides mobility of the pipe 38, in which the working position of the pipe 38 has a gap 63. When assembling and disassembling the impeller, the pipe 38 selects this gap 63, as described in the patent of the Russian Federation 2183747. In this case, the pipe 38 leaves coupling with the nozzle 5, ensuring the mobility of the blade 1 in the axial direction of the Christmas tree lock 16. The radial direction of the pipe 38 is maintained using the guide protrusion 34, while, when the rotor 19 is unwound, under the influence of centrifugal forces, the pipe 38 moves to the periphery in the radial direction, choosing a gap 62 to the joint of the sphere 40 and the cone 6. The number of holes 29 in the cover disk 27 and the pipelines 37, 38 corresponds to the number of working blades 1, as well as the guide protrusions 34 to the pipelines 38.

The working blades 1 are mounted on the rim 17 with a Christmas-tree lock 16 and are fixed with the help of the latch 22. The latch 22 is inserted between the locking hook 15 of the shank 13 of the working blade 1 and the hook 21 of the rim 17. The latch 22 is located in the peripheral part of the rim 17 of the disk 18, so that the Christmas the lock 16 having gaps 23 had a free exit on both sides of the disk 18. This provides cooling of the shank 13 of the working blade 1 and the rim 17 of the disk 18 with cooling air from the annular cavity 36 by blowing the gaps 23 of the Christmas tree lock 16 into the cavity behind the disk 18. Et The air from the annular cavity 36 is cooled by the feather of the blade 1 and its outlet edge 11. For air to pass to the radial channels 12 of the cooling system 8 of the blade 1 in the shank 13 of the working blade 1, an end trimming is made 14. The longitudinal channels 12 are connected to the internal cavity 9, from which air through the openings 10 in the outlet edge 11 of the blade 1 enters the path of the turbine 20. Cooling air enters the annular cavity 36 through the openings 30 in the cover disk 27. The peripheral radial cuts 33 are closed to these openings 30, providing unloading the cover disk 27 from thermal stresses. The cover disc 27 is profiled so that its peripheral part 26 is pressed against the ledge 24 of the labyrinth seal 25 under the action of centrifugal forces, providing the necessary tightness of the annular cavity 36. Cooling air enters the openings 30 from a twisting pneumatic device 55, to which air is supplied through the bypass pneumatic pipelines 49 in the inner housing 47 of the stator 43 and 48 in the straightening vanes 45 of the compressor 42. Air bypasses 48, 49 enter the bypass pneumatic pipelines from the compressor 42, previously cooled ny in the refrigerator 58. For this purpose the air cavity 46 of the pneumatic diffuser 56 through a first air inlet 59 is connected to the condenser 58 is connected to the input of a bypass air tube 48 to the first air outlet 60 which pneumatic line 57.

Here, another stream of cooling air is formed. The overflow pneumatic conduit 48 has an exit to the annular cavity 53 formed by the inner casing 47 of the stator 43 and the rotor part 50. This cavity is axially bounded by labyrinth seals 51, 52. The seal 51 is located behind the last stage of the compressor blades 42 under the straightener 44. the bypass pneumatic conduit 48 is located directly behind the seal 51. The seal 52 is not completely tight. The clearance 61 is calculated for the required air flow. Thus, the cooling air after the refrigerator 58 leaves the pneumatic conduit 48 into the annular cavity 53 and then passes the seal 52. In the annular cavity 53, the air is heated to cool the rotor part 50. After the seal 52, the air flows into the openings 29. The labyrinth seals 31, 32 prevent the overflow cooling air into the cavity in front of the cover disk. From the openings 29, air is passed through tubular pneumatic pipes 37, 38 through the nozzles 5 to the internal cavities 4 of the cooling system 2 of the inlet edge 3 of the blades 1. From the cavity 4, through the openings 7, the air enters the turbine path. In radial tubular pneumatic pipelines 37, 38, under the action of centrifugal forces, the air pressure rises, which ensures its exit to the increased pressure zone in front of the working blade 1. The air of the cooling system 2 cools the inlet edge 3, passing through the cavity 4 and participating in its cooling, displacing hot gases from the body of the blade 1 after its exit through the holes 7.

The rotor 41 of the compressor 42 is connected to the rotor 19 of the turbine 20 through the shank 35 of the cover disc 27 using fasteners 54, for which holes 28 are made in the shank 35 and the disk 18.

In comparison with known devices, the claimed device provides a more economical use of cooling refrigerant. Pre-cooling the air of cooling systems with its subsequent division into two streams ensures its rational use. The cost-effectiveness of the system is also to ensure the consistent use of air in cooling the rotor 50 and the blade 1. Partially using the refrigerant part of the air to cool the rotor 50, this air is further used in the cooling cooling of the blade 1, where its elevated temperature does not significantly affect the cooling efficiency. In this case, the loss of air pressure during the passage of the refrigerator 58, the pneumatic pipelines 56, 57, 48, the cavity 53 and the seal 52 is compensated for in the tubular pneumatic pipelines 37, 38.

The second cooling system is also rational 8. Since air from this system is discharged into the low-pressure cavity, it is possible in system 8 to use pre-cooled air of lower pressure. The use of cooling air in the low temperature system 8, after the refrigerator 58, ensures its low consumption, and this determines the increased efficiency of the cooling system.

The use of a disk mounted through a shank 35 using fasteners 54 on a small diameter provides reliable tightness of the cavity 36 and improves the strength characteristics of the disks in comparison with the known ones. The implementation of radial cuts 33, closed on the blown holes 30, and special profiling of the disk 27 with an emphasis on the ledge 24 successfully solves the same problems - strength and tightness.

The simplicity of assembling and disassembling the impeller of the turbine 20 is ensured by the mobility of the tubular pneumatic pipe 38 described above, and the implementation of these landings in the junction of the blade 1 and the pneumatic pipe 37 with the pneumatic pipe 38 ensures reliability and tightness of the joints. The existing experience confirms the reliability in the operation of this element both when carrying out locksmithing and during the regular operation of the turbine itself.

The placement of the heck 22 in the peripheral part 17 of the disk 18 and the shank 13 of the blade 1 provides locking of the blade 1 with guaranteed cooling of the shank of the blade and the peripheral rim of the disk.

Claims (6)

1. A device for cooling a rotor of a gas turbine, containing pneumatic piping, a refrigerator, cooled rotor blades with autonomous cooling systems of the inlet edge and the blade pen connected to channels in the shank, an annular screw pneumatic device, labyrinth seals and annular cavities, the first of which is formed by a stator and the rotor part between the compressor and the turbine, and the second - the cover disk and the impeller disk, characterized in that the flow part behind the compressor is connected by a pneumatic pipe and with the pneumatic inlet of the refrigerator, the pneumatic outlet of which is connected to the annular rotor cavity between the compressor and the turbine, which in the region of the turbine has a labyrinth seal with an increased gap, behind which in the cover disk there are a number of holes that are connected to the entrance to the telescopic tubular pneumatic pipelines, the output of each of which is connected to the inlet pipe of the channel of the cooling system of the inlet edge of the cooled working turbine blade, in addition, the pneumatic outlet of the refrigerator is connected to with a screw-on pneumatic device opposite the exit from which in the cover disk there is a series of holes with an exit to the annular cavity, which is connected to the longitudinal channels of the cooling system of the pen for working the turbine blades located in the shanks of the blades. 2. The device for cooling the rotor of a gas turbine according to claim 1, characterized in that a labyrinth seal is located behind the last working blade of the compressor under the rectifier, directly behind which there is an outlet of the pneumatic pipe connected to the pneumatic outlet of the refrigerator. 3. The device for cooling the rotor of a gas turbine according to claim 1, characterized in that the cover disk at the periphery in the axial direction rests on the cooled blade of the gas turbine and in the peripheral part has radial cuts that are closed to the holes into which air is supplied from the screw pneumatic device . 4. The device for cooling the rotor of a gas turbine according to claim 1, characterized in that the pneumatic pipe connecting the first row of holes in the cover disk to the pipe of the cooling channel of the inlet edge of the working blade consists of a radially arranged composite pipe in which the peripheral pipe is enclosed by a device restricting moving it except for the radial direction, and the peripheral pipe itself is connected to the profiled blade pipe in a cone-sphere and to the lower pipe telescopically so that the peripheral pipe has a the ability to freely move along its axis, radially to the axis of the engine, by the amount of entry into the cone-sphere connection. 5. The device for cooling the rotor of a gas turbine according to claim 1, characterized in that the shaped pipe of the cooling system of the inlet edge of the cooled blade is made l-shaped. 6. The device for cooling the rotor of a gas turbine according to claim 1, characterized in that the latch for locking the working blade is located on the periphery of the shank of the blade above the Christmas tree lock.

Images