CN113266468A - Hybrid electric propulsion method and device for three-shaft gas turbine engine - Google Patents
Hybrid electric propulsion method and device for three-shaft gas turbine engine Download PDFInfo
- Publication number
- CN113266468A CN113266468A CN202110691536.2A CN202110691536A CN113266468A CN 113266468 A CN113266468 A CN 113266468A CN 202110691536 A CN202110691536 A CN 202110691536A CN 113266468 A CN113266468 A CN 113266468A
- Authority
- CN
- China
- Prior art keywords
- gas generator
- turbine engine
- gas turbine
- motor
- gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 37
- 238000004088 simulation Methods 0.000 claims abstract description 32
- 238000004458 analytical method Methods 0.000 claims description 16
- 230000002427 irreversible effect Effects 0.000 claims description 7
- 238000005516 engineering process Methods 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 5
- 230000001276 controlling effect Effects 0.000 description 9
- 238000005457 optimization Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 230000006866 deterioration Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/81—Modelling or simulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/05—Purpose of the control system to affect the output of the engine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/20—Purpose of the control system to optimize the performance of a machine
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Eletrric Generators (AREA)
Abstract
The disclosure relates to the technical field of gas turbine engines, and discloses a hybrid electric propulsion method and device for a three-shaft gas turbine engine. The method utilizes a simulation model to simulate and determine the corresponding relation between the reduced rotating speed of the gas generator and the heat efficiency of the gas turbine engine by adjusting the power of the motor of the gas generator, and further determines the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator. The optimal reduced rotating speed of the gas generator determined by the hybrid electric propulsion method of the three-shaft gas turbine engine can improve the heat efficiency of the gas turbine engine, breaks through the limitation of the energy-saving effect of the existing hybrid electric propulsion technology by the battery capacity, greatly improves the power density of a hybrid electric propulsion system, reduces the system cost, and improves the non-design point efficiency of the engine under the condition of ensuring the balance of power supply and demand.
Description
Technical Field
The disclosure relates to the technical field of gas turbine engines, in particular to a hybrid electric propulsion method and device for a three-shaft gas turbine engine.
Background
The gas turbine engine has excellent performance, a series of advantages of high power-weight ratio, good acceleration, controllable emission pollution, good fuel adaptability and the like, is widely applied to the fields of ships, vehicles, aviation, gas transportation, thermal power generation and the like, and has wide market prospect. However, the problem of efficiency reduction of a non-design point of a gas turbine engine generally exists, and the root of the problem lies in that the common working point of each component is highly coupled with the load of the engine, and the one-to-one correspondence between the working point of each component and the output power is determined by the constraint relation between each component in pneumatic and mechanical aspects. With the reduction of the load, on one hand, the working condition point of the component deviates from the high-efficiency area, so that the efficiency of the component is reduced; on the other hand, the overall engine pressure ratio and the initial gas temperature decrease, resulting in a decrease in the Brayton cycle efficiency. The component efficiency and engine cycle efficiency degradation are direct causes of engine off-design point performance degradation.
Hybrid electric propulsion technology has been vigorously developed to improve gas turbine engine off-design point performance. At present, the hybrid electric propulsion technology disclosed at present mainly actively adjusts the load of an engine through a power battery, avoids the low-efficiency medium-low load working condition of the engine, but does not positively solve the problem of performance deterioration of the engine under the medium-low load. For scenarios with larger power levels, excessive battery capacity is required, with a large negative impact on both power system economy and power density.
Disclosure of Invention
The purpose of the present disclosure is to overcome the technical deficiencies, and provide a hybrid electric propulsion method for a three-shaft gas turbine engine, which realizes decoupling of the operating point of each component and the engine load, thereby optimizing the efficiency of the engine at the non-design point.
In order to achieve the above technical object, an aspect of the present disclosure provides a hybrid electric propulsion method for a three-shaft gas turbine engine, the three-shaft gas turbine engine including a gas generator and a power turbine, the gas generator including a high-pressure part and a low-pressure part, the high-pressure part including a high-pressure turbine, a high-pressure compressor, a high-pressure shaft, and a high-pressure shaft motor for controlling a rotation speed of the high-pressure shaft, the low-pressure part including a low-pressure turbine, a low-pressure compressor, a low-pressure shaft, and a low-pressure shaft motor for controlling a rotation speed of the low-pressure shaft, the hybrid electric propulsion method including:
obtaining component characteristic parameters of the gas turbine engine;
establishing a simulation model of the gas turbine engine based on the component characteristic parameters, the simulation model including an energy analysis module;
determining a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor comprising a high pressure shaft motor and/or a low pressure shaft motor, the reduced rotational speed of the gas generator comprising a reduced rotational speed of the high pressure shaft and a reduced rotational speed of the low pressure shaft, using the energy module of the simulation model;
and determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
Further, the gas turbine engine component characterization parameters include: pressure ratio and efficiency characteristics of the high pressure compressor, pressure ratio and efficiency characteristics of the low pressure compressor, expansion ratio and efficiency characteristics of the high pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, and expansion ratio and efficiency characteristics of the power turbine.
Further, the energy analysis module is configured to calculate an energy flow, a,
Flow and irreversible loss conditions.
Further, the hybrid electric propulsion means that, when the gas turbine engine is in operation, the gas generator motor is used as a motor to provide input power to the high-pressure shaft and/or the low-pressure shaft, or the gas generator motor is used as a generator to extract output power from the high-pressure shaft and/or the low-pressure shaft, so as to actively adjust the reduced rotation speed of the gas generator.
Further, determining an optimal reduced rotational speed of the gas generator and an optimal power of the gas generator motor according to a corresponding relationship between the reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine, comprising:
determining the reduced rotating speed of the gas generator corresponding to the optimal thermal efficiency as the optimal reduced rotating speed of the gas generator under the condition that the gas turbine engine is guaranteed not to exceed the rated working temperature, not to exceed the rated working rotating speed and the surge margin is not lower than the safety surge margin; determining the generator motor power corresponding to the optimal thermal efficiency as the optimal power
Further, the method further comprises:
and determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.
Further, the optimal power of the gas generator motor in said specific atmospheric environment needs to satisfy the following two conditions:
when the gas turbine engine is at 30% rated load, the thermal efficiency of the gas turbine engine is improved by more than 1%; and the number of the first and second groups,
and under the specific atmospheric environment, the gas turbine engine does not exceed the rated working temperature, does not exceed the rated working rotating speed, and has a surge margin not lower than a safety surge margin.
The technical scheme of this disclosure still provides a hybrid electric propulsion device of three-shaft gas turbine engine, the three-shaft gas turbine engine includes gas generator and power turbine, gas generator includes high-pressure part and low pressure part, the high-pressure part has high-pressure turbine, high-pressure compressor, high-pressure axle and the high-pressure axle motor of controlling the high-pressure axle rotational speed, the low pressure turbine has low-pressure turbine, low-pressure compressor, low-pressure axle and the low-pressure axle motor of controlling the low-pressure axle rotational speed, the hybrid electric propulsion controlling means includes:
an acquisition module for acquiring component characteristic parameters of the gas turbine engine;
a modeling module for building a simulation model of the gas turbine engine based on the component property parameters, the simulation model including an energy analysis module;
a first determining module, configured to determine a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor including a high-pressure shaft motor and/or a low-pressure shaft motor, the reduced rotational speed of the gas generator including the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft, using the energy module of the simulation model;
and the second determination module is used for determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
Further, the hybrid electric propulsion control device further comprises a third determination module, which is used for determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.
Compared with the prior art, the hybrid electric propulsion method of the three-shaft gas turbine engine disclosed by the invention has at least one or part of the following beneficial effects:
(1) the rotating speed of the gas generator (high-pressure shaft and low-pressure shaft) is decoupled from the load of the engine, and the rotating speed and the common working point of the gas generator (high-pressure shaft and low-pressure shaft) can be regulated within a certain range under the condition of ensuring the output power of the gas turbine engine to be certain by regulating the input power or the output power of the motor of the gas generator.
(2) By performing simulation, the effectiveness of the hybrid electric propulsion scheme can be verified.
(3) The present disclosure enables optimization of off-design point operating conditions, particularly gas turbine engine component efficiency and cyclic thermal efficiency at medium to low loads, reducing part count
Loss, effectively relieving the efficiency deterioration problem under the low load in the engine.
(4) The energy-saving effect of the hybrid electric propulsion system is not limited by battery capacity, and the performance of the engine at a non-design point is improved under the condition of ensuring the balance of power supply and demand, so that the hybrid electric propulsion system is suitable for high-power scenes such as ships, thermal power generation, main passenger planes and the like, the battery capacity in the hybrid electric propulsion system is effectively reduced, and the power density and the economy of the system are improved.
Drawings
FIG. 1 is a schematic illustration of a three-shaft gas turbine engine in an embodiment of the present disclosure;
FIG. 2 is a flow chart of a hybrid electric propulsion method of a three-shaft gas turbine engine according to an embodiment of the present disclosure;
FIG. 3 is a block level simulation model and energy analysis module for a three-axis gas turbine engine built in Simulink;
FIG. 4 shows the results of energy analysis of the hybrid electric propulsion method applied to a three-axis gas turbine of FIG. 1 at 40% load, simulating the energy flow and irreversible loss of the components;
FIG. 5 shows the gas turbine efficiency and parts before and after the hybrid electric propulsion method of the present invention is applied to a three-shaft gas turbine of FIG. 1 at 40% load
A loss condition. Under the working condition, the scheme effectively reduces the exhaust loss of the gas turbine and improves the thermal efficiency by 2 percent;
FIG. 6 is a schematic structural view of a hybrid electric propulsion device of a three-shaft gas turbine engine according to the present disclosure.
Detailed Description
In order to make the objects, technical solutions and advantages of the present disclosure more clearly understood, the present disclosure is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the disclosure and are not intended to limit the disclosure.
Gas turbine engines include gas turbines and aircraft engines, split shaft gas turbines and turboshaft engines generally include a gas generator including a combustor, a compressor, and a compressor turbine, and a power turbine. In operation, the compressor draws air into the interior of the gas turbine engine and compresses the air. The compressed air and fuel are mixed and combusted in the combustion chamber, the generated high-temperature and high-pressure gas pushes the turbine blades to rotate, one part of power is used for driving the power turbine to output power outwards, and the other part of power drives the compressor to rotate through the compressor turbine. Therefore, the output power of the gas turbine engine is highly coupled with the rotating speed of the compressor, and the working points of all the parts are in one-to-one correspondence with the output power according to the pneumatic and mechanical constraint relations among all the parts. According to the hybrid electric propulsion method, the decoupling of the working condition points of all parts and the load of the engine is realized, so that the efficiency of the engine at a non-design point is optimized.
Fig. 1 is a schematic view of a three-shaft gas turbine engine in an embodiment, as shown in fig. 1, including a gas generator including a combustor, a high-pressure compressor, a low-pressure compressor, a high-pressure turbine, and a low-pressure turbine, and a power turbine.
The high-pressure component is provided with a high-pressure compressor, a high-pressure turbine, a high-pressure shaft and a high-pressure shaft motor for controlling the rotating speed of the high-pressure shaft, and the low-pressure component is provided with a low-pressure compressor, a low-pressure turbine, a low-pressure shaft and a low-pressure shaft motor for controlling the rotating speed of the low-pressure shaft. Specifically, the high-pressure turbine drives the high-pressure compressor through the high-pressure shaft, and the low-pressure turbine drives the low-pressure compressor through the low-pressure shaft. The high-pressure shaft motor is arranged on the high-pressure shaft, the rotating speed of the high-pressure shaft can be controlled by controlling the input power or the output power of the high-pressure shaft motor, the low-pressure shaft motor is arranged on the low-pressure shaft, and the rotating speed of the low-pressure shaft can be controlled by controlling the input power or the output power of the low-pressure shaft motor.
FIG. 2 is a flow chart of a hybrid electric propulsion method for a three-shaft gas turbine engine according to an embodiment of the present disclosure.
As shown in fig. 2, a hybrid electric propulsion method of a three-shaft gas turbine engine includes:
step S1: obtaining component characteristic parameters of the gas turbine engine;
step S2: establishing a simulation model of the gas turbine engine based on the component characteristic parameters, the simulation model including an energy analysis module;
step S3: determining a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor comprising a high pressure shaft motor and/or a low pressure shaft motor, the reduced rotational speed of the gas generator comprising a reduced rotational speed of the high pressure shaft and a reduced rotational speed of the low pressure shaft, using the energy module of the simulation model;
step S4: and determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
The method utilizes an energy module of a simulation model, determines the corresponding relation between the reduced rotating speed of the gas generator and the heat efficiency of the gas turbine engine by adjusting the power of the motor of the gas generator, determines the influence rule of the reduced rotating speed of the gas generator on the whole engine performance, and further determines the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator. The optimal power is input or extracted to the high-pressure shaft and/or the low-pressure shaft, the rotating speed of the high-pressure shaft and/or the low-pressure shaft is actively adjusted, the reduced rotating speed of the high-pressure shaft and the low-pressure shaft is optimized, and the decoupling of the rotating speed and the load of the gas generator of the gas turbine engine is realized. The optimal reduced rotating speed of the gas generator determined by the hybrid electric propulsion method of the three-shaft gas turbine engine can improve the heat efficiency of the gas turbine engine, breaks through the limitation of the energy-saving effect of the existing hybrid electric propulsion technology by the battery capacity, greatly improves the power density of the hybrid electric propulsion system, reduces the system cost, and improves the non-design point efficiency of the engine under the condition of ensuring the balance of power supply and demand.
In some embodiments, a hybrid electric propulsion method for a three-shaft gas turbine engine, comprises:
step S1: obtaining component characteristic parameters of the gas turbine engine.
Specifically, the high-pressure compressor, the low-pressure compressor, the high-pressure turbine, the low-pressure turbine and the power turbine component characteristic diagram can be determined by calculating fluid three-dimensional simulation or component characteristic experiments. From the component property map, a component property parameter of the gas turbine engine may be determined. Wherein the gas turbine engine component characteristic parameters may include: pressure ratio and efficiency characteristics of the high pressure compressor, pressure ratio and efficiency characteristics of the low pressure compressor, expansion ratio and efficiency characteristics of the high pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, and expansion ratio and efficiency characteristics of the power turbine.
Step S2: establishing a simulation model of the gas turbine engine based on the component property parameters, the simulation model including an energy analysis module.
Specifically, on the basis of the component characteristics in step 1, a component-level simulation model is established, and an energy analysis module is added in the simulation model. The energy analysis module is configured to calculate an energy flow, a,
Flow and irreversible lossThe method is described. The components of the gas turbine engine may be a high pressure compressor, a low pressure compressor, a high pressure turbine, a low pressure turbine and a power turbine. FIG. 3 is a block diagram of a three-axis gas turbine component level simulation model and energy analysis module built in Simulink.
Step S3: determining a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor using the energy module of the simulation model, the reduced rotational speed of the gas generator including a reduced rotational speed of the high pressure shaft and a reduced rotational speed of the low pressure shaft.
Wherein the gasifier motor comprises a high pressure shaft motor and/or the low pressure shaft motor, and the reduced gasifier rotational speed comprises a reduced rotational speed of the high pressure shaft and/or a reduced rotational speed of the low pressure shaft.
Hybrid electric propulsion means that when the gas turbine engine works, the electric machine serves as a motor to provide input power to the high-pressure shaft and/or the low-pressure shaft, or the electric machine serves as a generator to extract power from the high-pressure shaft and/or the low-pressure shaft, so that the reduced rotating speed of the gas generator is actively adjusted, and decoupling control of the rotating speed of the high-pressure shaft and the rotating speed of the low-pressure shaft and the load of the engine is realized.
When the method is implemented, the energy analysis module of the simulation model constructed in the step S3 is used to change the reduced rotation speed NH of the high-pressure shaft by adjusting the input/output power of the high-pressure shaft and/or the low-pressure shaftcorAnd low spool reduced speed NLcorThereby calculating the reduced rotation speed NH of different high-pressure shaftscorAnd low spool reduced speed NLcorIn combination, the energy flow of the components of the gas turbine engine,
Flow and irreversible losses, and determining the correspondence between the reduced rotation speed of the gas generator and the thermal efficiency of said gas turbine engine.
Specifically, as shown in FIG. 4, a specific high-pressure shaft reduced speed is calculated for the gas turbine engine at 40% load condition, for exampleNHcorAnd low spool reduced speed NLcorIn combination, the energy flow of the components of the gas turbine engine,
Flow and irreversible loss conditions. Calculating different high-pressure shaft reduced rotating speeds NH by adjusting the motor powers of different gas generatorscorAnd low spool reduced speed NLcorThe corresponding relationship between the reduced gas generator speed and the thermal efficiency of the gas turbine engine at 40% load of the gas turbine engine can be determined.
In some embodiments, the operating conditions of the gas turbine engine at 10%, 20%, 30%, 40%, 50%, 60%, 70%, 80%, 90%, 100% load, respectively, may also be calculated to determine the correspondence between the reduced rotational speed of the gas generator and the thermal efficiency of the gas turbine engine at different loads.
Step S4: and determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
Specifically, under the condition that the gas turbine engine is guaranteed not to exceed a rated working temperature, not to exceed a rated working rotating speed and the surge margin is not lower than a safe surge margin, the reduced rotating speed of the gas generator corresponding to the optimal thermal efficiency is determined as the optimal reduced rotating speed of the gas generator; and determining the power of the generator motor corresponding to the optimal thermal efficiency as the optimal power.
In practice, the target reduced gasifier speed can be achieved by adjusting the gasifier motor power, thereby determining the optimum power of the gasifier motor.
FIG. 5 shows the energy analysis results for the three shaft gas turbine hybrid electric propulsion scheme at 40% load. As shown in fig. 5, the left graph is the situation before optimization, and the right graph is the situation after optimization, it can be seen that different folded rotation speeds of the high pressure shaft and/or the low pressure shaft can result in different thermal efficiencies of the engine. In the right diagram, the high-pressure shaft and the low-pressure shaft of the gas generator are controlled at the optimal reduced rotating speed, the motor of the gas generator is adjusted to the optimal power, and the heat efficiency of the engine is improved by 2%.
In other embodiments, the optimal reduced rotation speed of the gas generator and the optimal power of the motor of the gas generator under different loads can be determined according to the corresponding relationship between the reduced rotation speed of the gas generator under different loads and the thermal efficiency of the gas turbine engine, so that the high-pressure shaft and the low-pressure shaft are both at the optimal reduced rotation speed under different loads, the optimal reduced rotation speed can achieve the optimal efficiency under the condition that the engine is not over-heated or over-rotated and enough surge margin is ensured, the irreversible loss of a gas turbine engine system under different loads is reduced, and the oil consumption rate of an un-designed point is reduced.
The simulation calculation is carried out in a standard atmospheric environment, the engine load is reduced to a reduced parameter under a standard working condition, and the optimization result of the control rule is the corresponding optimal NH under different loadscor、NLcorThe value is obtained. Optimal NH at different reduced loads by gas generator motor during operation of gas turbinecor、NLcorAnd (4) closed-loop control.
In some embodiments, after determining the optimal power for the gas turbine engine gas generator motor, the hybrid electric propulsion method further comprises:
step S5: and determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator. The atmospheric environment includes, but is not limited to, gas turbine engine inlet total temperature and total pressure, among others.
The optimal power of the generator motor for a specific atmospheric environment must satisfy the following two conditions:
when the gas turbine engine is at 30% rated load, the thermal efficiency of the gas turbine engine is improved by more than 1%; and
and under the atmospheric pressure condition, the gas turbine engine does not exceed the rated working temperature, does not exceed the rated working rotating speed, and the surge margin is not lower than the safety surge margin.
When the method is realized, the motor power of the high-pressure shaft and/or the low-pressure shaft is input, whether the reduced rotating speed of the gas generator meets the optimal reduced rotating speed or not is verified, the efficiency improving effect of the gas turbine under the reduced power is realized, whether the temperature is over-temperature and the rotation is over-high or not is judged, and whether the surge margin meets the requirement or not is verified.
Because the influence of the motor power on the engine performance and the reduced rotating speed of the gas generator is different for different atmospheric temperatures and atmospheric pressures, the reduced power of the different atmospheric temperatures and atmospheric pressures can be converted according to the following formula:
reduced power
Where p is the output power, Tin、PinTotal gas turbine engine inlet temperature and total pressure.
Fig. 6 is a schematic structural view of a hybrid electric propulsion control apparatus of a three-shaft gas turbine engine, which includes, referring to fig. 6: the system comprises an acquisition module 201, a modeling module 202, a first determination module 203 and a second determination module 204.
An acquisition module for acquiring component characteristic parameters of the gas turbine engine;
a modeling module for building a simulation model of the gas turbine engine based on the component property parameters, the simulation model including an energy analysis module;
a first determining module, configured to determine a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor including a high-pressure shaft motor and/or a low-pressure shaft motor, the reduced rotational speed of the gas generator including the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft, using the energy module of the simulation model;
and the second determination module is used for determining the optimal reduced rotating speed of the gas generator and the optimal power of the gas generator motor according to the corresponding relation between the reduced rotating speed of the gas generator and the heat efficiency of the gas turbine engine.
Further, the hybrid electric propulsion control apparatus further includes:
and the third determining module is used for determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.
In the hybrid electric propulsion control device provided in the above embodiment, only the division of the functional modules is illustrated in the electric propulsion control, and in practical applications, the functions may be distributed to different functional modules as needed, that is, the internal structure of the device may be divided into different functional modules to complete all or part of the functions. In addition, the hybrid electric propulsion method of the three-shaft gas turbine engine provided by the embodiment belongs to the same concept, and specific implementation processes are detailed in the method embodiment and are not described again.
So far, the embodiments of the present disclosure have been described in detail with reference to the accompanying drawings. It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. Further, the above definitions of the various elements and methods are not limited to the various specific structures, shapes or arrangements of parts mentioned in the examples, which may be easily modified or substituted by those of ordinary skill in the art.
From the above description, those skilled in the art should have a clear understanding of the present disclosure of gas turbine engine hybrid electric propulsion schemes based on gas generator speed decoupling.
In summary, the present disclosure determines the power of the gas generator motor and the engine components through simulation
And determining the influence rule of the loss corresponding relation on the whole machine performance, and determining the optimal power of the gas generator motor of the gas turbine engine. Namely byInputting or extracting optimal power to the high-pressure shaft and/or the low-pressure shaft, actively adjusting the rotating speed of the high-pressure shaft and/or the low-pressure shaft, optimizing the reduced rotating speed of the high-pressure shaft and the low-pressure shaft, and realizing the decoupling of the rotating speed and the load of the gas generator of the gas turbine engine. The hybrid electric propulsion method of the three-shaft gas turbine engine disclosed by the invention can break through the limitation of the energy-saving effect of the existing hybrid electric propulsion technology by the battery capacity, greatly improve the power density of the hybrid electric propulsion system, reduce the system cost and improve the efficiency of the non-design point of the engine under the condition of ensuring the balance of power supply and demand.
Claims (9)
1. A hybrid electric propulsion method for a three-shaft gas turbine engine, the three-shaft gas turbine engine including a gas generator and a power turbine, the gas generator including a high pressure component having a high pressure turbine, a high pressure compressor, a high pressure shaft, and a high pressure shaft motor for controlling a rotation speed of the high pressure shaft, and a low pressure component having a low pressure turbine, a low pressure compressor, a low pressure shaft, and a low pressure shaft motor for controlling a rotation speed of the low pressure shaft, the hybrid electric propulsion method comprising:
obtaining component characteristic parameters of the gas turbine engine;
establishing a simulation model of the gas turbine engine based on the component characteristic parameters, the simulation model including an energy analysis module;
determining a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor comprising a high pressure shaft motor and/or a low pressure shaft motor, the reduced rotational speed of the gas generator comprising a reduced rotational speed of the high pressure shaft and a reduced rotational speed of the low pressure shaft, using the energy module of the simulation model;
and determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
2. The hybrid electric propulsion method of claim 1, wherein the gas turbine engine component characteristic parameters include: pressure ratio and efficiency characteristics of the high pressure compressor, pressure ratio and efficiency characteristics of the low pressure compressor, expansion ratio and efficiency characteristics of the high pressure turbine, expansion ratio and efficiency characteristics of the low pressure turbine, and expansion ratio and efficiency characteristics of the power turbine.
3. The hybrid electric propulsion method of claim 1, wherein an energy analysis module is configured to calculate an energy flow, a thrust force, and a thrust force of a component of the gas turbine engine using a first law and a second law of thermodynamics,
Flow and irreversible loss conditions.
4. The hybrid electric propulsion method of claim 1, wherein the hybrid electric propulsion is such that, when the gas turbine engine is operating, the gas generator motor acts as a motor to provide input power to the high pressure shaft and/or the low pressure shaft, or the gas generator motor acts as a generator to extract output power from the high pressure shaft and/or the low pressure shaft to actively adjust the folded rotation speed of the gas generator.
5. The hybrid electric propulsion method of any one of claims 1 to 4, wherein determining the optimum reduced speed of the gas generator and the optimum power of the gas generator motor based on the correspondence between the reduced speed of the gas generator and the thermal efficiency of the gas turbine engine comprises:
determining the reduced rotating speed of the gas generator corresponding to the optimal thermal efficiency as the optimal reduced rotating speed of the gas generator under the condition that the gas turbine engine is guaranteed not to exceed the rated working temperature, not to exceed the rated working rotating speed and the surge margin is not lower than the safety surge margin; and determining the power of the generator motor corresponding to the optimal thermal efficiency as the optimal power.
6. The hybrid electric propulsion method of any one of claims 1 to 4, further comprising:
and determining the optimal power of the gas generator motor under different specific atmospheric environments according to the optimal reduced rotating speed of the gas generator.
7. Hybrid electric propulsion method according to claim 6, characterized in that the optimal power of the gas generator motor in said specific atmospheric environment is such as to satisfy the following two conditions:
when the gas turbine engine is at 30% rated load, the thermal efficiency of the gas turbine engine is improved by more than 1%; and
and under the specific atmospheric environment, the gas turbine engine does not exceed the rated working temperature, does not exceed the rated working rotating speed, and has a surge margin not lower than a safety surge margin.
8. A hybrid electric propulsion device for a three-shaft gas turbine engine, the three-shaft gas turbine engine including a gas generator and a power turbine, the gas generator including a high pressure part having a high pressure turbine, a high pressure compressor, a high pressure shaft, and a high pressure shaft motor for controlling a rotation speed of the high pressure shaft, and a low pressure part having a low pressure turbine, a low pressure compressor, a low pressure shaft, and a low pressure shaft motor for controlling a rotation speed of the low pressure shaft, the hybrid electric propulsion control device comprising:
an acquisition module for acquiring component characteristic parameters of the gas turbine engine;
a modeling module for building a simulation model of the gas turbine engine based on the component property parameters, the simulation model including an energy analysis module;
a first determining module, configured to determine a corresponding relationship between a reduced rotational speed of the gas generator and a thermal efficiency of the gas turbine engine by adjusting a power of a gas generator motor, the gas generator motor including a high-pressure shaft motor and/or a low-pressure shaft motor, the reduced rotational speed of the gas generator including the reduced rotational speed of the high-pressure shaft and the reduced rotational speed of the low-pressure shaft, using the energy module of the simulation model;
and the second determination module is used for determining the optimal reduced rotating speed of the gas generator and the optimal power of the motor of the gas generator according to the corresponding relation between the reduced rotating speed of the gas generator and the thermal efficiency of the gas turbine engine.
9. The hybrid electric propulsion device of a three-shaft gas turbine engine according to claim 8, characterized in that it further comprises a third determination module for determining the optimal power of the generator motor in different specific atmospheric environments, according to the optimal reduced rotation speed of the generator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110691536.2A CN113266468B (en) | 2021-06-22 | 2021-06-22 | Hybrid electric propulsion method and device for three-shaft gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110691536.2A CN113266468B (en) | 2021-06-22 | 2021-06-22 | Hybrid electric propulsion method and device for three-shaft gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113266468A true CN113266468A (en) | 2021-08-17 |
| CN113266468B CN113266468B (en) | 2022-06-21 |
Family
ID=77235625
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110691536.2A Active CN113266468B (en) | 2021-06-22 | 2021-06-22 | Hybrid electric propulsion method and device for three-shaft gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113266468B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970446A (en) * | 2021-11-18 | 2022-01-25 | 中国船舶重工集团公司第七O三研究所无锡分部 | Method for determining thermal efficiency of marine gas turbine based on air intake and exhaust system |
| CN114635801A (en) * | 2022-03-23 | 2022-06-17 | 合肥工业大学 | Method and device for optimizing backpressure characteristic of gas generator |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0950808A2 (en) * | 1998-04-13 | 1999-10-20 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| WO2003060303A1 (en) * | 2002-01-09 | 2003-07-24 | Ebara Corporation | A gas turbine apparatus and a starting method thereof |
| CN1849444A (en) * | 2003-09-12 | 2006-10-18 | 麦斯国际有限公司 | Multi-spool turbogenerator system and control method |
| CN101457695A (en) * | 2007-12-10 | 2009-06-17 | 阿尔斯通技术有限公司 | Method for controlling a gas turbine in a power plant and power plant for carrying out the method |
| CN101509426A (en) * | 2009-03-31 | 2009-08-19 | 严政 | Turbine shaft engine |
| US20110101693A1 (en) * | 2009-11-04 | 2011-05-05 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft starter generator |
| US20150135722A1 (en) * | 2013-11-18 | 2015-05-21 | Mitsubishi Hitchi Power Systems, Ltd. | System and method of controlling a two-shaft gas turbine |
| EP2878795A1 (en) * | 2013-11-27 | 2015-06-03 | Airbus Operations GmbH | Engine for propelling an aircraft and aircraft having at least one engine and at least one hydrogen tank |
| CN105756782A (en) * | 2016-04-15 | 2016-07-13 | 浙江大学 | Solar chemically recuperated gas turbine system and method implemented by same |
| CN106468219A (en) * | 2015-08-14 | 2017-03-01 | 通用电气公司 | Gas-turbine unit stall margin manages |
| EP3231711A1 (en) * | 2016-04-11 | 2017-10-18 | General Electric Company | Electric propulsion engine for an aircraft |
| US20170363099A1 (en) * | 2016-06-20 | 2017-12-21 | United Technologies Corporation | Engine bleed air system with waste gate valve for compressor surge management |
| US20180002025A1 (en) * | 2016-07-01 | 2018-01-04 | United Technologies Corporation | Aircraft including parallel hybrid gas turbine electric propulsion system |
| CN109083748A (en) * | 2018-07-24 | 2018-12-25 | 中国科学院工程热物理研究所 | Become the high-power control method of geometry three shaft gas turbine |
| CN109204840A (en) * | 2017-06-30 | 2019-01-15 | 通用电气公司 | Propulsion system for aircraft |
| GB201908374D0 (en) * | 2019-06-12 | 2019-07-24 | Rolls Royce Plc | Limiting spool speeds in a gas turbine engine |
| CN111488668A (en) * | 2019-01-29 | 2020-08-04 | 波音公司 | Aircraft Auxiliary Power Unit (APU) control system with speed compensation |
| US20200248619A1 (en) * | 2019-02-05 | 2020-08-06 | United Technologies Corporation | Transient operation control of a hybrid gas turbine engine |
-
2021
- 2021-06-22 CN CN202110691536.2A patent/CN113266468B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0950808A2 (en) * | 1998-04-13 | 1999-10-20 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| WO2003060303A1 (en) * | 2002-01-09 | 2003-07-24 | Ebara Corporation | A gas turbine apparatus and a starting method thereof |
| CN1849444A (en) * | 2003-09-12 | 2006-10-18 | 麦斯国际有限公司 | Multi-spool turbogenerator system and control method |
| CN101457695A (en) * | 2007-12-10 | 2009-06-17 | 阿尔斯通技术有限公司 | Method for controlling a gas turbine in a power plant and power plant for carrying out the method |
| CN101509426A (en) * | 2009-03-31 | 2009-08-19 | 严政 | Turbine shaft engine |
| US20110101693A1 (en) * | 2009-11-04 | 2011-05-05 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft starter generator |
| US20150135722A1 (en) * | 2013-11-18 | 2015-05-21 | Mitsubishi Hitchi Power Systems, Ltd. | System and method of controlling a two-shaft gas turbine |
| EP2878795A1 (en) * | 2013-11-27 | 2015-06-03 | Airbus Operations GmbH | Engine for propelling an aircraft and aircraft having at least one engine and at least one hydrogen tank |
| CN106468219A (en) * | 2015-08-14 | 2017-03-01 | 通用电气公司 | Gas-turbine unit stall margin manages |
| EP3231711A1 (en) * | 2016-04-11 | 2017-10-18 | General Electric Company | Electric propulsion engine for an aircraft |
| CN105756782A (en) * | 2016-04-15 | 2016-07-13 | 浙江大学 | Solar chemically recuperated gas turbine system and method implemented by same |
| US20170363099A1 (en) * | 2016-06-20 | 2017-12-21 | United Technologies Corporation | Engine bleed air system with waste gate valve for compressor surge management |
| US20180002025A1 (en) * | 2016-07-01 | 2018-01-04 | United Technologies Corporation | Aircraft including parallel hybrid gas turbine electric propulsion system |
| CN109204840A (en) * | 2017-06-30 | 2019-01-15 | 通用电气公司 | Propulsion system for aircraft |
| CN109083748A (en) * | 2018-07-24 | 2018-12-25 | 中国科学院工程热物理研究所 | Become the high-power control method of geometry three shaft gas turbine |
| CN111488668A (en) * | 2019-01-29 | 2020-08-04 | 波音公司 | Aircraft Auxiliary Power Unit (APU) control system with speed compensation |
| US20200248619A1 (en) * | 2019-02-05 | 2020-08-06 | United Technologies Corporation | Transient operation control of a hybrid gas turbine engine |
| GB201908374D0 (en) * | 2019-06-12 | 2019-07-24 | Rolls Royce Plc | Limiting spool speeds in a gas turbine engine |
Non-Patent Citations (6)
| Title |
|---|
| WANG, T等: "Real-Time Variable Geometry Triaxial Gas Turbine Model for Hardware-in-the-Loop Simulation Experiments", 《JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME》 * |
| 丁明等: "复合能源分布式发电系统的机组组合问题", 《电力系统自动化》 * |
| 周文太等: "混联式混合动力汽车高速工况经济性研究", 《汽车技术》 * |
| 孔祥浩等: "分布式电推进飞机电力系统研究综述", 《航空学报》 * |
| 王涛等: "动力涡轮导叶可调的三轴式船用燃气轮机动态实时仿真", 《推进技术》 * |
| 臧述升等: "三轴燃气轮机动态性能模块化仿真", 《计算机仿真》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970446A (en) * | 2021-11-18 | 2022-01-25 | 中国船舶重工集团公司第七O三研究所无锡分部 | Method for determining thermal efficiency of marine gas turbine based on air intake and exhaust system |
| CN114635801A (en) * | 2022-03-23 | 2022-06-17 | 合肥工业大学 | Method and device for optimizing backpressure characteristic of gas generator |
| CN114635801B (en) * | 2022-03-23 | 2023-11-21 | 合肥工业大学 | Back pressure characteristic optimization method and device for gas generator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113266468B (en) | 2022-06-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113266468B (en) | Hybrid electric propulsion method and device for three-shaft gas turbine engine | |
| CA2902461C (en) | Hybrid turbo electric aero-propulsion system control | |
| US8141360B1 (en) | Hybrid gas turbine and internal combustion engine | |
| Guda et al. | A simulink-based microturbine model for distributed generation studies | |
| US9388737B2 (en) | Aero boost—gas turbine energy supplementing systems and efficient inlet cooling and heating, and methods of making and using the same | |
| US20130318965A1 (en) | Supercharged Combined Cycle System With Air Flow Bypass To HRSG And Hydraulically Coupled Fan | |
| JP2003314291A (en) | Exhaust driven engine cooling system | |
| CN101509426B (en) | Turbine shaft engine | |
| CN114991959B (en) | Flexible and efficient peak shaving system and method for coupling compressed air energy storage of gas turbine | |
| EP2964922B1 (en) | Capacity control of turbine by the use of a reheat combustor in multishaft engine | |
| Hao et al. | Off-design performance of 9F gas turbine based on gPROMs and BP neural network model | |
| CN114462245B (en) | Multi-shaft gas turbine optimal rotation speed determination method and system | |
| CN115685752A (en) | Modeling method of intercooling gas turbine model based on modular simulation platform | |
| CN114427975A (en) | Tandem type combined power mode conversion verification method | |
| Saddiq et al. | Modelling of gas turbine and gas turbine exhaust and its utilisation as combined cycle in utility system | |
| Long et al. | Research on active modulation of gas turbine cooling air flow | |
| Malozemov et al. | Hybrid power system with variable speed diesel engine | |
| CN114483309A (en) | Electrically-controlled variable-cycle double-shaft gas turbine hybrid power system | |
| CN203925754U (en) | Have to the supercharging combined cycle system of the bypass of gas flow of HRSG and fan | |
| CN114781088A (en) | Gas turbine starting process simulation method based on speed increasing rate | |
| CN113104220A (en) | Multi-electric hybrid power system | |
| Kowalski et al. | Performance analysis of gas turbine air heat recovery unit using GateCycle software | |
| CN116451363A (en) | Control method and device for guide vane-free counter-rotating turbine engine based on rotational speed decoupling | |
| CN114635801B (en) | Back pressure characteristic optimization method and device for gas generator | |
| Wei et al. | Dynamic simulation and control strategy for three-shaft marine electric propulsion gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |