Adjustment device of alignment of synchronising control ring of rotating blades of gas-turbine engine, and gas-turbine engine

IPC classes for russian patent Adjustment device of alignment of synchronising control ring of rotating blades of gas-turbine engine, and gas-turbine engine (RU 2420663):

F04D29/56 - adjustable

F01D9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits

F01D17/16 - by means of nozzle vanes

Another patents in same IPC classes:

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Antiwear device for guide roller of blade with variable setting angle in compressor of gas-turbine engine, compressor of gas-turbine engine and gas-turbine engine / 2420662

FIELD: engines and pumps.

SUBSTANCE: adjustment device of alignment of control ring of rotating blades of gas-turbine engine relative to cylindrical casing of crankcase includes control ring containing multiple threaded holes made in radial direction and multiple holders of blocks, each of which includes threaded bar screwed into one of threaded holes of the ring. On inner end of each block holder there installed is the block intended to come into contact with cylindrical casing. In addition, control ring includes multiple slots having tangential direction and passing through the ring in radial direction. Each slot is interconnected with one of threaded holes of the ring. Device has also compression means of each of the slots in longitudinal direction in order to lock the position of block holders. Other invention of the group refers to gas-turbine engine containing the above adjustment device of alignment of control ring of rotating blades.

EFFECT: inventions allow simplifying the alignment device of control ring and improving its reliability, and accurate alignment of control ring of rotating blades is provided.

5 cl, 5 dwg

The technical field

The present invention relates to the field of devices for adjusting the alignment of the synchronization control ring rotatable blades of a gas turbine engine on its axis.

Prior art

Known use in gas turbine engine of one or more rows of stator blades for adjusting the direction of flow of gases passing through the compression section, depending on the mode of operation of the gas turbine engine. These rows of stator blades contain many blades (called blades with changing angle), which can be rotated about its axis of connection to the stator in such a way as to change the installation angle depending on the operating mode of the gas turbine engine.

Known control devices rotary blades usually contain a ring covering the cylindrical casing of the crankcase gas turbine engine, and the many levers or rods, with each rod includes a first end connected to the control ring by means of a hinge, and a second end mounted on the pivot pin of the corresponding blade. Simultaneous change of the angular position of the blades is performed by the rotation of the ring around the axis of the gas turbine engine.

The center of the ring control vanes located on the axis of the gas turbine d is". In addition, it is installed coaxially with the casing of the crankcase gas turbine engine and relies on the crankcase, usually by means of a set of pads, evenly distributed over its entire circumference.

To improve the accuracy of the installation angle of the stator blades is necessary to ensure perfect coaxiality between the control ring and casing respectively. Ideal coaxiality can be achieved by maintaining a small gap between the pads and the casing respectively. To obtain a small gap device used for mounting pads on the control ring should allow to adjust the pads in the radial direction.

In the device control coaxially control ring, as a rule, use pads that are installed on the threaded rods are screwed up in the control ring. From patent US 5387080 known pads, radial position which regulate using the two-way screw mounted on the ring and containing two plot threads with different angle turns.

The adjusting device pads in the ring control does not allow you to achieve the perfect locking of the threaded rod of the adjustment pads on all phases of operation of the gas turbine engine. Indeed, when some blocks away from the casing respectively, when vibration occurs, the wear of the thread of the adjusting rod that p is igodit to the violation of the adjustment pads and therefore, the vibration control ring, which particularly affect the accuracy of the installation angle of the blades.

The invention

The present invention is to eliminate the above disadvantages of the known devices by creating a device control coaxially control ring, which is simple in construction and reliable in all phases of the gas turbine engine.

In connection with this object of the present invention is a device for adjusting the centering of the control ring rotatable blades of a gas turbine engine, and the control ring contains a number of threaded holes formed in the radial direction, and many holders of pads, each of which contains a threaded rod, screw in one of the tapped holes of the ring, with the inner end of each holder pads pad set designed to enter into contact with the cylindrical casing, characterized in that the control ring further comprises a number of gaps having a tangential direction and passing through the ring in the radial direction, each slit communicates with one of the threaded holes of the ring, and the device comprises means of compression of each of the slits in the longitudinal direction to about the level lock position holders pads.

Adjustment of the pads in the radial direction is carried out with the help of more or less screwing the threaded rod in the control ring. After adjusting the position of the rod holder pad lock by squeezing slit in the longitudinal direction. Thus, this adjusting device contains a small number of parts, which makes the design simple, and provides a reliable locking pads, regardless of the phase of operation of the gas turbine engine.

Preferably, the means squeezing included lots of holes formed in the control ring in the longitudinal direction, and each hole was reported with one of the slots of the ring, and the device contained many bolted joints, each of which was Sabinillas in one of the holes of the ring, by compression of the corresponding slit in the longitudinal direction.

It is preferable that each slit was one of its tangential ends in one of the tapped holes of the control ring. In this case, each slit can extend its tangential end opposite the threaded hole in the smooth channel passing through the control ring in the radial direction.

The object of the present invention is a gas turbine engine containing at measures which, one of the above-described adjustment of the centering of the control ring rotatable blades.

Brief description of drawings

Other distinctive features and advantages of the present invention will be more apparent from the following description given with reference to the accompanying drawings, illustrating, not limiting example of implementation, including:

Figure 1 represents a schematic view of the stage rotary vane ring control.

Figure 2 is a view in isometric of the adjusting device in accordance with the present invention before Assembly.

Figure 3 is a view in isometric of the adjusting device shown in figure 2, after Assembly.

4 and 5 are views in section of the adjusting device shown in figure 3, respectively, in the longitudinal plane and in a radial plane.

A detailed description of the scenarios

Figure 1 is a partially shown, the compressor of the gas turbine engine. The compressor includes a casing 10 of the stator with its center on the longitudinal axis x-X of the gas turbine engine, covering the rotor 12, limiting with him the ring circuit 14 of the gas stream.

The compressor further comprises a set of blades, forming several rows in the circuit 14 of the gas stream. Some of these series consist of blades 16 with changing angle. These blades 16 with the rotation around the radial axis 18, passing through the stator casing 10.

Each axis (or the swivel pin) of the blades 16 with the changing angle at which the one end is connected with a thrust of 20 or lever by means of the handpiece 22. The other end of the rod 20 pivotally mounted on the pins 24, made in the radial direction on the control ring 26. The latter comprises a cylindrical casing 28 of the crankcase gas turbine engine with a center on the longitudinal axis x-X of the engine. The control ring 26 and the cylindrical casing 28 are mounted concentrically relative to each other.

The object of the present invention is a device that allows you to adjust the centering ring 26 of the control relative to the longitudinal axis x-X of the gas turbine engine. In particular, such a device can maintain a fixed radial gap between the control ring 26 and the cylindrical casing 28 of the crankcase gas turbine engine.

As shown in figure 2-5, the adjusting device centering ring 26 control in accordance with the present invention contains, in particular, many of the pads 30, which are intended to enter into contact with the cylindrical casing 28 boats gas turbine engine.

The pads 30 are evenly distributed around the entire circumference of the ring 26 and control are, for example, between two adjacent pins 24 (Fig 1).

Each deck is 30 still connected with the inner end of the holder 32 pads, for example, by pressing on the end. Each holder pads 32 includes a threaded rod 34, which is screwing in the screw hole 36 made through the control ring 26 in a radial direction relative to the ring. After screwing in the ring control rod 34 of the holder 32 of the pad comes out of the ring in the radial direction (figure 3 and 5).

According to the invention, the control ring 26 further comprises a number of gaps 38, having a tangential (or circumferential) direction and passing through the ring through in the radial direction. In addition, each slit 38 is connected with one of the threaded holes 36 of the ring.

In the example of execution shown in figure 2-5, communication between the cracks and screw holes of the control ring is due to the fact that each slit 38 extends one of its tangential ends into the corresponding threaded hole 36 of the ring.

The adjusting device centering ring 26 control in accordance with the present invention further comprises means squeezing each of the slits 38 in the longitudinal direction to provide locking position holders 32 pads.

For this purpose, the ring 26 control contains many holes 40 (e.g., smooth), performed in the longitudinal direction (i.e. parallel to the longitudinal axis x-X ha is turbinado engine) each of which communicates with one of the slots 38 of the ring.

In the example of execution shown in figure 2-5, communication between the cracks and holes of the control ring is due to the fact that, as shown in figure 4, each hole 40 passes through one of the slots 38 is essentially perpendicular to the crack.

The device also contains many bolted joints 42, each of which screw up in one of the holes 40 of the ring, with each bolt connection 42 includes a screw 42A and protracted nut 42b.

When the nut 42b on the screw 42A, screwed into one of the holes 40, is compressed in the longitudinal direction of the corresponding slots 38 (in other words, the slit 38 tends to deform, as shown by the arrows in figure 4). This compression of the slit provides locking of the respective holder 32 pads. Thus, in this type of device there is no need to use nuts, pull on the free end of the threaded rod.

It should be noted that the nearer the hole 40, in which screwing the screw 42A is (in the tangential direction) to the threaded hole 36, in which screwing the threaded rod 34 of the respective holder pads, the better is the compression and, therefore, lock the position of the holder block.

You will also note the, each of the slits 38 may extend its tangential end opposite the threaded hole 36 of the passage of the threaded rod 34, in a smooth channel 44, passing through the control ring 26 in the radial direction. These smooth channels 44 are designed to provide machining of slots 38 (indeed, a tool for processing of slots must achieve both the tangential ends of the slits).

Adjustment of the radial position of each pad 30 relative to the cylindrical casing 28 is carried out by more or less screwing the threaded rod 34 of the holder 32 pads into the corresponding threaded hole 36 of the ring 26 to control. After reaching the optimum position of the pads 30, the screws 42 are screwed up in the corresponding hole 40 and the nut 42b tighten on its free end, blocking, thus, by squeezing the holder 32 of the pad in its optimum position. Through this adjustment for each block that is installed on the control ring, it is possible to center the ring along the longitudinal axis x-X of the gas turbine engine.

1. The adjusting device centering ring (26) control rotary blades (16) of the gas turbine engine relative to the cylindrical casing (28) crankcase gas turbine engine, and the ring (26) control contains sets the threaded holes (36), made in the radial direction, and a plurality of holders (32) blocks, each of which contains a threaded rod (34), screw in one of the tapped holes (36) of the ring, with the inner end of each holder (32) pads set block (30)intended to enter into contact with the cylindrical casing (28), characterized in that the ring (26) control further comprises multiple slits (38)having a tangential direction and passing through the ring in the radial direction, each slit (38) communicates with one of the threaded holes (36) of the ring, and the device comprises means (40, 42) of compression of each of the slits (38) in the longitudinal direction to provide locking position holders (32) blocks.

2. The device according to claim 1, characterized in that the means of compression include a number of holes (40), is performed on the ring (26) management in the longitudinal direction, each of which communicates with one of the slots (38) rings, and many bolted joints (42), each of which screw up in one of the holes (40) rings ensure sdabrivaniya corresponding slit (38) in the longitudinal direction.

3. Device according to one of claims 1 or 2, characterized in that each slot (38) is one of its tangential ends in one of the tapped holes (36) of the ring (26) controls the expression.

4. The device according to claim 3, characterized in that each slot (38) is tangential end opposite the threaded hole (36)in a smooth channel (44)passing through the ring (26) control in the radial direction.

5. Gas turbine engine containing at least one adjusting device centering ring (26) control the turning vanes (16) according to any one of claims 1 to 4.