Control system of stages of rotating blades of stator of compressor of gas turbine engine

IPC classes for russian patent Control system of stages of rotating blades of stator of compressor of gas turbine engine (RU 2422644):

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:

Adjustment device of alignment of synchronising control ring of rotating blades of gas-turbine engine, and gas-turbine engine / 2420663

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Stator blade with alternate angle of assembly, gas turbine motor with such blade and procedure for repair of such blade / 2416725

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Row of blades of straightening device driven with rotary ring of automatic centring, compressor equipped with said row of blades and gas-turbine motor containing this compressor / 2416724

Jacket contains stationary coaxial circular rail projecting from external surface of this jacket. Also, at least three movable parts spaced one from another in circumferential direction can travel along this rail. Each movable part is connected with the driven ring by means of a radial guiding structure. For each movable part the radial guiding structure contains an element in form of a rod installed in radial direction into an orifice made in the said ring. The rod-shaped element is secured on the movable part. Another invention of the group refers to a compressor equipped with at least one above said row of the blades of the straightening device with alternate angles of assembly. One more invention refers to the gas-turbine motor incorporating the said compressor.

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Gas turbine engine and its intermediate assembly / 2396436

Gas turbine engine comprises intermediate assembly 14 to be arranged axially between turbine 1^st and 2^nd assemblies. The latter can represent LP compressor and HP compressor or HP turbine and LP turbine. Said intermediate assembly comprises circular channel 5c running around central axial line 18 of intermediate assembly 14. Intermediate assembly serves to direct gas flow from gas channel in the 1^st assembly to that in the 2^nd assembly. Inlet 19 of said circular gas channel 5c of intermediate assembly is notably shifted radially relative to its outlet 20. Intermediate assembly circular gas channel 5c accommodates at least one guide element 28, 29 to direct gas flow. Said guide element features the shape of circular guide element and is located nearby curved section of the wall that forms circular gas channel.

Adjustment device of alignment of synchronising control ring of rotating blades of gas-turbine engine, and gas-turbine engine / 2420663

FIELD: engines and pumps.

SUBSTANCE: control system of stages of rotating blades of stator of compressor of gas turbine engine includes drive shaft including driving arm connected through a rod to power cylinder of control mechanism, and the arm connected through a rod to sensor of setting angle of rotating blades. Driving arm includes outer and inner arms connected at two points by means of the first and the second fasteners. Inner arm has the possibility of being rotated relative to the second fixture in case of damage of the first fixture. Rods of power cylinder and sensor have the possibility of being moved in parallel planes, and sensor is directly connected to automatic control system of gas turbine engine.

EFFECT: invention allows improving reliability of control system owing to obtaining reliable information on actual position of rotating blades of stator.

2 cl, 3 dwg

The invention relates to the field of aviation and gas turbine plants for terrestrial applications, namely high pressure compressor turbojet engines and methods of speed control of the rotary blades of the stator of the compressor.

Improvement of the parameters of the engine, in particular, increase engine efficiency and reduce fuel consumption, requires improving the efficiency of the compressor and the expansion of the range of stable operation. One of the ways to increase the efficiency of the compressor is the expansion of the variance of angles and ranges of angles of rotation of the blades of the guide blade apparatus-speed compressor high pressure transient modes of engine operation from start up to maximum thrust, including emergency, and unsteady modes. One of the main conditions engine performance over the entire range of modes of operation is the reliability of all the individual elements of the mechanism of rotation of the blades, guide vanes.

Known control system the speed of the rotary blades of the stator of the compressor of the gas turbine engine via a drive mechanism rotating the inlet guide vanes (BHA) engine PS-90A in which the rotor angle sensor installation the rotary blades by means of rods connected with the leading arm the m drive shaft (Sea, Iaaneem, Dee, Alexander Neradko, Aaiasb. Aircraft engine PS-90A, M.: Libra, 2007, p.57).

Upon breakage of the lead arm is impossible to obtain reliable information about the actual position of the rotary blades of the stator of the compressor, since in this case would violate the relationship between the angle sensor installation the rotary blades and by the turning blades.

Closest to the proposed management system is the speed of the blades of the stator turbojet engine with a variable angle, including the power mechanism by rods and levers associated with a synchronizing ring control, which in turn is connected with each of the rotary blades of the stator of the compressor of the gas turbine engine (Application for invention No. 2006116817, F02K 3/00, 2007).

When you increase the load on the lift mechanism may break parts and violation of the kinematic relations between the power cylinder and drive shaft. This will lead to spontaneous install turning vanes in an indeterminate angle and, ultimately, to surge, emergency stop engine and compressor failure.

The technical problem which is solved by the invention is to improve system reliability by preventing failure of the compressor in case of violation of the kinematic relations between the power cylinder and drive shaft by means of obtaining reliable information about the actual position of the rotary blades of the stator, coming into the automatic control system of gas turbine engine.

The invention consists in that the control system the speed of the rotary blades of the stator of the compressor of the gas turbine engine with a control mechanism associated with each rotary blade speed through the drive shaft with the lever according to claim 1 of formula drive shaft further includes a leading arm, which is connected with the power cylinder control mechanism by means of traction and contains outer and inner levers connected in two places using the first and second fastening elements, with the inner lever is configured to rotate relative to the second fastening element in case of failure of the first fastening element and the stator housing fixed angle sensor installation the rotary blades associated with the lever drive shaft through a thrust sensor, while the traction force of the vehicle and the sensor is arranged to move in parallel planes, and the sensor is directly connected with the automatic control system of gas turbine engine.

In addition, according to claim 2 of the formula first and second fastening elements on the strength characteristics vary at least 3 times. The first element is the so-called "weak link" of the inner lever, which in the first ocher is d ' breaks down when loading.

In case of failure of the first fastening element ("weak link") and violation of the kinematic relations between the power cylinder and drive shaft speed of the rotary blades of the stator of the compressor will be saved kinematic connection sensor installation angle of the rotary blades themselves blades that will provide reliable information about the actual position of the rotary blades. And in the case of achieving the limit values of the mismatch between the software value of the angle of the blades and the actual characterizing the range becompany operation of the compressor, depending on the mode of operation of the engine automatic control system generates a signal to run lock, or on the termination of the startup or shutdown of the engine. This protects the compressor from damage due to surge.

In addition, it becomes possible to objectively analyze the situation that led to the halt or stop run or the run lock. In case of breakage of the fastening element of the internal lever enables quick replacement of this element directly in the operation.

Figure 1 shows the stage rotary vane compressor stator of a gas turbine engine, figure 2 is a view As in figure 1. Figure 3 presents the leading lever drive shaft speed of the rotary blades.

In the stator to compress the ora gas turbine engine placed guides blade apparatus with rotating blades 1 compressor stator, on the outer pins are fixed swing arms 2. The lever 2 is pivotally connected with a synchronizing rings 3 adjustable rods 4, the drive shaft 5 and power 6 cylinder control mechanism rotary blades 1. The driving shaft 5 includes leading the lever 7 and the arms 8, United articulated rods 9 of the power cylinder 6 rods 10 sensor 11 installation angle of the rotary blade 1, as well as rods 4 connected with a synchronizing rings 3. Thrust 9 and 10 is arranged to move in parallel planes.

Leading the lever 7 includes outer 12 and inner levers 13, United in two places using the first 14 and second 15 of the fastening elements. The first element 14 (the"weak link") on the strength of lower than 15 second, at least 3 times. The inner lever 13 is made to rotate relative to the second fastening element 15 in case of failure of the first element 14, the "weak link". The rotation of the blades 1 is carried out simultaneously from the power cylinder 6, the efforts which are transmitted simultaneously on adjustable thrust levers 9 and 7, synchronously rotating drive shaft 5. The shaft 5 interacts hinge connections of the levers 8 with adjustable rods 4 and through the swivel rotates the synchronizing ring 3 around the axis of the stator of the compressor.

A synchronizing ring 3 pivotally connected with rotimi levers 2 and in turn interact with external pins of the rotary blades 1, providing the required angles of the guide vanes 1 in all modes of operation of the compressor of the gas turbine engine.

The system works as follows.

In the case of a significant increase in load on the details of the control mechanism of the rotary blades 1 and violations of the kinematic connection between the power cylinder 6 and the drive shaft 5 is broken "weak link" 14 leading arm 7. The internal lever 13 rotates about the axis of the second fastening element 15, thereby maintaining the kinematic connection between the blades 1 of the stator and the sensor 11. In the case of achieving the limit values of the mismatch between the software angle α_onthe program and the actual value of α_oncharacterizing the range becompany operation of the compressor depending on the mode of operation of the engine, the automatic control system generates a signal to lock or termination of the startup or shutdown of the engine. This ensures protection against breakage of parts of the compressor from surging.

In addition, it becomes possible to obtain reliable information about the actual position of the rotary blades of the stator, allowing to analyze the situation that led to the stop, start or termination of the lock start engine.

After engine shutdown and elimination in the in a significant increase in the load on the lift mechanism enables quick replacement of the first fastening element 14 (the"weak link") and start the engine.

1. Control system the speed of the rotary blades of the stator of the compressor of the gas turbine engine with a control mechanism associated with each rotary blade speed by the drive shaft of the levers, wherein the drive shaft further includes a leading arm, which is connected with the power cylinder control mechanism by means of traction and contains outer and inner levers connected in two places using the first and second fastening elements, with the inner lever is configured to rotate relative to the second fastening element in case of failure of the first fastening element and the stator housing fixed angle sensor installation the rotary blades associated with the lever drive shaft through thrust sensor, while the traction force of the vehicle and the sensor is arranged to move in parallel planes, and the sensor is directly connected with the automatic control system of gas turbine engine.

2. Control system the speed of the rotary blades of the stator of the compressor of the gas turbine engine according to claim 1, characterized in that the first and second fastening elements on the strength characteristics vary at least 3 times.