RU2481564C1 - Jet-turbine engine, test method of jet-turbine engine, production method of batch of jet-turbine engines (versions), and operating method of jet-turbine engine - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: test methods of jet-turbine engines (JTE) are described in the group of inventions. When performing the test steps, alteration of the modes, which exceed as to duration the programmed flight time, is performed. Typical flight cycles are formed, based on which damageability of the most loaded parts is determined as per the programme. The required number of loading cycles during the test is determined. Full scope of tests is formed, including a quick change of cycles in the complete register from quick selection of maximum or full augmented power mode of the engine, and then, representative cycle of continuous operation with multiple alteration of modes in the whole working spectrum with various span of range of the mode change, which exceeds the flight time at least by 5-6 times. Quick selection of maximum or augmented power mode in some part of the test cycle is performed at the rate of acceleration and discharge.

EFFECT: development of test methods of aircraft jet-turbine engines with improved reliability of test results at any of the steps from an experimental-industrial specimen to industrial production and flight operation of aircraft engines.

8 cl

Description

A group of inventions related by a single creative concept relates to the field of aircraft engine manufacturing, namely to turbojet aircraft engines, their testing methods, experimental and industrial production and operation.

There is a method of testing a turbojet engine to determine the resource and reliability, which consists in the alternation of modes when performing stages lasting longer than the flight time. The engine is tested in stages. The duration of non-stop work at the stand and the alternation of modes are set depending on the purpose of the engine (L.S. Skubachevsky. Test of jet engines. Moscow, Engineering, 1972, p.13-15).

The known method is characterized by the greatest duration and energy consumption of tests with bringing to complete destruction of individual engines.

A well-known turbojet engine, which is double-circuit, contains a housing supported by compressors and turbines, a cooled combustion chamber, a fuel-pump group, jet nozzles and a control system with command and executive bodies (Shulgin V.A., Gaysinsky S.Ya. Double-circuit turbojet engines of low-noise aircraft. M: ed. Mashinostroenie, 1984, pp. 17-120).

There is a known method for the development and testing of aircraft turbojet engines, which consists in measuring parameters according to engine operating conditions and bringing them to standard atmospheric conditions, taking into account changes in the properties of the working fluid and the geometric characteristics of the engine’s flow part when atmospheric conditions change (Yu.A. Litvinov, V.O. . Borovik. Characteristics and operational properties of aircraft turbojet engines. M.: Mashinostroenie, 1979, 288 s, pp. 136-137).

A known method for the development and testing of aircraft engines such as turbojet, including the development of specified modes, parameter monitoring and evaluation of resource and reliability of the engine. In order to reduce the test time during engine refinement of 10-20%, tests are carried out with the gas temperature in front of the turbine exceeding the maximum operating temperature by 45-65 ° C (SU 1151075 A1, publ. 10.08.2004).

A known method of industrial production of aircraft engines such as turbojet, including the manufacture and factory assembly of power, control, command and executive units, engine blocks and systems, including compressors, turbines, combustion chambers, air, fuel and oil systems and engine control systems. (Boguslaev V.A., Kachan A.Ya., Dolmatov A.I., Mozgovoy V.F., Korenevsky N.Ya. Production technology of aircraft engines Zaporozhye. Published. Motor Sich, 2009 [textbook]; part 4 Assembly of aircraft engines Section 3, p.26-61.

A known method of operating aircraft engines such as turbojet engines, including maintenance operations, pre-flight preparation, start-up, warm-up, output to flight regimes stipulated by the regulations and engine shutdown, as well as prevention, maintenance and overhauls. (Yu.A. Litvinov, V.O. Borovik. Characteristics and operational properties of aircraft turbojet engines. M: Mechanical Engineering, 1979, p. 288).

Common shortcomings of these known technical solutions are the increased labor and energy intensity of tests and an insufficiently high estimate of the resource and reliability of the engine in a wide range of flight modes and operating conditions, due to the inadequacy of the program for bringing specific test results to results assigned to standard engine operating conditions by known methods, which do not take into account with sufficient accuracy a change in the parameters and operating modes of the engine. This complicates the possibility of bringing the experimental test parameters to the parameters that are as close as possible to the real structure and the specific ratio of the engine operating modes during operation, at each of the stages of development, development, pilot production, serial production and operation of aircraft engines.

The objective of the invention is to develop aircraft engines such as turbojet, methods for testing, refinement, pilot and industrial production and operation with increased reliability of test results at any stage from the pilot design to the industrial production and flight operation of aircraft engines, including the inclusion development of typical flight cycles, determining the resource and reliability of the engine in conditions as close as possible to the real structure and specific ratio of presses of the engine during operation.

The task in part of the method for testing a turbojet engine (turbojet engine) is solved by the fact that according to the invention includes the alternation of modes when performing the stages of the test with a duration of operation of the turbojet engine exceeding the programmed flight time, for which typical flight cycles are first formed and the damageability of the most loaded parts is determined based on this determine the required number of loading cycles during the test, and then form and produce the full scope of the tests, including the implementation of Sequences of test cycles — quick exit to maximum or full forced mode, quick reset to “low gas” mode, stop and long-term operation cycle with multiple alternating modes in the entire operating spectrum with a different range of variation of the turbojet engine operating modes, in total exceeding the flight time 5 ÷ 6 times; at the same time, a different range of changes in the engine operating modes is realized by changing the level of the gas differential in specific test modes from the initial to the maximum - maximum or full forced engine operation by transferring the initial reference point when performing the corresponding mode, taking the latter in one of the modes in position the corresponding “low gas” level, and in other modes - in intermediate or final positions corresponding to different percentages or the full value of the level gas of maximum or full forced mode, and a quick exit to maximum or forced modes on part of the test cycle is carried out at a rate of pick-up with subsequent reset.

At the same time, part of the test cycles can be carried out without warming up in the "low gas" mode after starting.

The test cycle can be formed on the basis of flight cycles for combat and training use of a turbojet engine.

The task in terms of the production method of a batch of turbojet engines in which an experimental batch of turbojet engines is performed, at least each experimental engine is assembled, including mounting a housing, turbines with rotors supported on it, compressors, a fuel and pump group, a jet nozzle, mainly with a changing critical cross section and a thrust vector, a cooled combustion chamber and a control system with command and executive bodies and test mounted experimental turbofan engines on a test The resource and reliability in the conditions of multi-mode flights are solved by the fact that according to the invention, the tests are performed using the turbofan engine test method described above, upon completion of the test program, they analyze the results obtained, eliminate the identified shortcomings, if necessary, make changes to the design or to individual components of the turbofan engine and consider the prototype executed and corresponding to the given program.

The problem in terms of a turbojet engine is solved by the fact that according to the invention the engine is double-circuit, contains a housing, turbines with rotors supported on it, compressors, a fuel-pump group, a jet nozzle with a changing critical cross section and a thrust vector, a cooled combustion chamber and a control system with command and executive bodies, while the engine, at least at one of the stages - fine-tuning, pilot production, mass production and / or operation, was tested nnym TRD above test method to determine the life and reliability of the program reproducing conditions as close as possible to the real structure and the ratio of specific predetermined engine operation modes.

The task in terms of a method of manufacturing a batch of turbojet engines, in which at least a serial industrial factory assembly of the engines is carried out, with each engine having a housing and power units, including compressors, turbines, at least one combustion chamber, a jet nozzle, air, fuel and oil hydraulic systems, monitoring, command and actuating elements, blocks and systems, and perform bench tests of serial turbojet engines from a batch identically of the produced turbojet engines, it is decided that, according to the invention, a group of engines from an industrial batch of turbojet engines is subjected to testing and the tests are carried out using the aforementioned test method for turbojet engines to determine the service life and reliability, and they check the compliance of these resources with the specified values, if necessary, followed by the translation of the test results obtained in specific atmospheric and climatic conditions, to values corresponding to standard atmospheric conditions, with the possibility of subsequent recount results, if necessary, to any required atmospheric and climatic conditions for which this or that serial engine or a batch of simultaneously manufactured identical turbojet engines is intended.

The set task in terms of the method of operation of a turbojet engine, in which before each start they check the readiness of the engine for operation, start, warm up and bring the engine to the operating modes specified in the regulations, periodically perform routine inspections, current repairs, as well as at least one overhaul, it is decided that according to the invention, after overhaul, the engine is subjected to bench tests by the above method for testing turbojet engines for determining the res ca and reliability of the engine, the results of which, if necessary, fine-tuning and post-repair, if necessary, the variant perform additional tests, correlated with the thematic content posleremontnogo finishing and regulations of the next stage of operation of the turbojet engine.

Moreover, after overhaul and / or after-repair tuning, the turbojet engine can be subjected to a surge test and determination of the boundaries of the gas-dynamic stability of the work.

The technical result provided by the given set of features consists in the development of test methods at the stages of performing prototypes, refinement, as well as at the stage of serial turbojet engines manufactured and overhauled, which increase the reliability of test results, which is achieved due to the alternation of modes developed in the invention when performing test steps that are longer in duration than the programmed flight time, ipovye flight cycles, based on which the program is determined defectiveness most loaded parts and based on this determine the required number of cycles in the test. The full scope of the tests is formed, including the quick change of cycles in the full register from the quick exit to the maximum or full forced mode to the complete stop of the engine and then a representative long-term operation cycle with multiple alternating modes in the entire operating spectrum with a different range of regime change exceeding the flight time not exceeding less than 5 times, moreover, a quick exit to the maximum or forced mode on part of the test cycle is carried out at the rate of throttle response and reset. This makes it possible to simplify subsequent tests, increase the correctness and expand the representativeness of resource estimates and engine reliability at all stages of development, serial production and flight operation of turbojet engines with the correct distribution of representative estimates to a wide range of regional and seasonal conditions for subsequent flight operation of engines performed in accordance with with the invention.

In the proposed method for testing a turbojet engine, the tests are carried out with alternating modes and the duration of the engine exceeding the programmed flight time. First, typical flight cycles are formed and damage to the most loaded parts is determined. The required number of loading cycles during the test is determined. The full scope of the tests is formed and performed, including the execution of a sequence of test cycles - quick exit to the maximum or full forced mode, quick reset to the "low gas" mode, stop. A cycle of long work is performed with multiple alternation of modes in the entire working spectrum with a different range of variation in the operating modes of a turbojet engine exceeding the flight time by 5–6 times. A different range of changes in the engine operating modes is realized by changing the level of the gas drop in specific test modes from the initial to the maximum - maximum or full forced engine operation, by transferring the initial reference point when performing the corresponding mode, taking the latter in one of the modes in the position corresponding to “low gas” level, and in other modes - in intermediate or final positions corresponding to different percentages or the full value of the gas level full or forced mode. A quick exit to the maximum or forced modes on the part of the test cycle is carried out at the rate of throttle response, followed by reset.

Part of the test cycles is carried out without warming up in the "low gas" mode after starting.

The test cycle is formed on the basis of flight cycles for combat and training use of a turbojet engine.

In the production method of a batch of turbojet engines in which an experimental batch of turbojet engines is performed, at least an assembly of each experimental engine is produced. Mount the housing, turbines with rotors supported on it, compressors, a fuel and pump group, a jet nozzle, mainly with a changing critical cross section and a thrust vector, a cooled combustion chamber and a control system with command and executive bodies. Next, they test the mounted experimental turbofan engines to determine the resource and reliability in multi-mode flights. The tests are performed by the above method of testing turbofan engines. Upon completion of the test program, the results obtained are analyzed, and the identified shortcomings are eliminated. If necessary, make changes to the design or to individual nodes of the turbojet engine and consider the prototype completed and corresponding to a given program.

The turbojet engine is double-circuit, contains a housing, turbines with rotors supported on it, compressors, a fuel-pumping group, a jet nozzle with a changing critical section and a thrust vector, a cooled combustion chamber and a control system with command and executive bodies. The engine, at least at one of the stages of fine-tuning, pilot production, mass production and / or operation, was tested by the test method described above for determining the resource and reliability of a program for reproducing conditions that are as close as possible to the real structure and specific ratio of the specified modes engine operation.

In the production method of a batch of turbojet engines, at least a serial industrial factory engine assembly is carried out. In each engine, a body and power units are mounted, including compressors, turbines, at least one combustion chamber, a jet nozzle, air, fuel and oil hydraulic systems, monitoring, command and actuating elements, blocks and systems. Perform bench tests of serial turbojet engines from a batch of identically produced turbojet engines. A group of engines from an industrial batch of turbojet engines is tested and tested using the above method of testing turbojet engines for determining the resource and reliability of operation. Check the compliance of these resources with the specified values. If necessary, transfer the test results obtained in specific atmospheric and climatic conditions to the values corresponding to standard atmospheric conditions, with the possibility of subsequent recalculation of the final results, if necessary, to any required atmospheric and climatic conditions for which this or that serial engine is intended or a batch of simultaneously manufactured identical turbojet engines.

In the method of operating a turbojet engine, before each start, a check is made of the readiness of the engine for operation. Start, warm up and output the engine to the operating modes specified in the regulations. Periodically perform preventive examinations, ongoing repairs, as well as at least one overhaul. After major repairs, the engine is subjected to bench tests using the above method of testing a turbojet engine after major repairs during the operation of the turbojet engine to determine the resource and reliability of the engine. According to the test results, if necessary, post-repair debugging is carried out and, if necessary, additional tests are variant performed, correlated with the thematic content of post-repair debugging and the regulations of the subsequent stage of operation of a turbojet engine.

After overhaul and / or after-repair tuning, the turbojet engine is subjected to a surge test and determination of the boundaries of the gas-dynamic stability of the work.

An example implementation of a test method for a turbojet engine (turbojet engine)

A turbojet engine with a design resource of 500 hours of total running time is tested, until the first overhaul. In the specified resource, the operating time is set to 20 hours at maximum mode, of which 5 hours at full forced mode. Typical flight cycles (TFCs) are formed and a predetermined engine operating time of 1 h is set, which is equivalent to the flight time of an aircraft (LA) according to the adopted TOC. Based on the fuel processing center, the damage to the most loaded parts is determined by calculation. On the basis of this, the required equivalent damage number of cycles during the tests is determined. In this embodiment, the following set of load test cycles is taken - performing 700 (400 + 300) starts with reaching the maximum and forced modes, respectively, as well as 400 pick-ups from the “low gas” (MG) mode to the maximum (Max.) And 300 from the mode 0.8 max. before the forced (For) mode.

Set the safety factor for the required number of test load cycles and operating hours K = 1, 2.

Form the full scope of life tests and develop a test program.

1. The total operating time during the life tests is 500 * 1.2 = 600 hours, of which the maximum operating time is (20-5) * 1.2 = 18 hours, and in the forced mode 5 * 1.2 = 6 hours .

2. Take the duration of the test phase 5 hours, and determine the number of five-hour steps 600: 5 = 120.

3. Set the number of starts taking into account the safety factor of 700 * 1.2 = 840, as well as from MG to Max 400 * 1.2 = 480 and from 0.8 Max to Fore 300 * 1.2 = 360.

4. Each five-hour stage includes 840: 120 = 7, pick-ups from the MG mode to Max 480: 120 = 4 and pick-ups from the 0.8 Max mode to For 360: 120 = 3, as well as the operating time at maximum and forced modes 18 * 60 : 120 = 9 min; 360: 120 = 3 min.

5. Set the sequence of test cycles - quick exit to maximum or full forced mode, quick reset to MG mode and stop. Then, a long-term operation cycle is provided with multiple alternation of load cycles with a range of regime change ranges from MG to Max and 0.8 Max to For within the range of the test stages established above.

Perform tests of turbofan engines according to the specified program. Then the engine is faulted and the test results are analyzed, according to which a decision is made to recognize the engine as tested.

The above test sequence of turbojet engines is used at all stages from the development of prototypes to industrial production, operation and overhaul of engines.

Claims (8)

1. A test method for a turbojet engine (turbojet engine), characterized in that it includes the alternation of modes during the execution of the test stages with a duration of operation of the turbojet engine exceeding the programmed flight time, for which typical flight cycles are first formed and the damageability of the most loaded parts is determined, based on which the necessary the number of loading cycles during the test, and then form and produce the full scope of the tests, including the execution of the sequence of test cycles c - a quick exit to the maximum or full forced mode, a quick reset to the “low gas” mode, a stop and a long operation cycle with multiple alternating modes in the entire operating spectrum with a different range of variation in the operating modes of a turbojet engine, in total exceeding a flight time of 5 -6 times; at the same time, a different range of changes in the engine operating modes is realized by changing the level of the gas differential in specific test modes from the initial to the maximum - maximum or full forced engine operation by transferring the initial reference point when performing the corresponding mode, taking the latter in one of the modes in position the corresponding “low gas” level, and in other modes - in intermediate or final positions corresponding to different percentages or the full value of the level gas of maximum or full forced mode, and a quick exit to maximum or forced modes on part of the test cycle is carried out at a rate of pick-up with subsequent reset. 2. The method of testing a turbojet engine according to claim 1, characterized in that part of the test cycles is carried out without heating in the "small gas" mode after starting. 3. The method of testing a turbojet engine according to claim 1, characterized in that the test cycle is formed on the basis of flight cycles for military and educational use of the turbojet engine. 4. A method of manufacturing a batch of turbojet engines, in which an experimental batch of turbojet engines is carried out, and a case is mounted, turbines with rotors supported on it, compressors, a fuel-pump group, a jet nozzle with mainly varying critical cross-section and thrust vector, a cooled combustion chamber and system control with the command and executive bodies and test mounted experimental turbofan engines to determine the resource and reliability in multi-mode flights, characterized in that the tests are performed with manual according to any one of claims 1 to 3, upon completion of the test program, analyze the results obtained, eliminate the identified deficiencies, if necessary, make changes to the design or to individual components of the turbojet engine and consider the prototype completed and corresponding to the given program. 5. A turbojet engine, characterized in that it is double-circuit, contains a housing, turbines with rotors supported on it, compressors, a fuel-pump group, a jet nozzle with a changing critical cross section and a thrust vector, a cooled combustion chamber and a control system with command and executive organs, while the engine, at least at one of the stages of fine-tuning, pilot production, mass production and / or operation, is subjected to tests by the method according to any one of claims 1-3 to determine the resource and ezhnosti program playback conditions as close as possible to the real structure and the ratio of specific predetermined engine operation modes. 6. A method of manufacturing a batch of turbojet engines, in which at least a serial industrial factory assembly of the engines is carried out, with each engine mounting a body and power units, including compressors, turbines, at least one combustion chamber, a jet nozzle, an air nozzle, fuel and oil hydraulic systems, monitoring, command and actuating elements, blocks and systems, and they perform bench tests of serial turbojet engines from a batch of identically produced turbojet engines, distinguishing Take into account that a group of engines from an industrial batch of turbojet engines is subjected to testing, tests are carried out by the method according to any one of claims 1-3 to determine the resource and reliability of the operation, and they verify the compliance of these resources with the specified values, if necessary, followed by the translation of the test results obtained in specific atmospheric conditions -climatic conditions, to values corresponding to standard atmospheric conditions, with the possibility of subsequent recalculation of the final results, if necessary, to any desired atmosphere climatic conditions for operation in which one or another serial engine or a batch of simultaneously manufactured identical turbojet engines is intended. 7. A method of operating a turbojet engine, in which, before each start-up, a check is made of the engine's readiness for operation, the engine is started, warmed up and output is switched to the operating modes specified in the regulations, periodic inspections, routine repairs, and at least one overhaul are performed , characterized in that after the overhaul of the engine is subjected to bench tests by the method according to any one of claims 1 to 3 to determine the resource and reliability of the engine, according to which and the need to produce a post-repair finishing and, if necessary, the variant perform additional tests, correlated with the thematic content posleremontnogo finishing and regulations of the next stage of operation of the turbojet engine. 8. The method of operating a turbojet engine according to claim 7, characterized in that after overhaul and / or after-repair tuning, the turbojet engine is subjected to a surge test and determination of the boundaries of gas-dynamic stability of work.