CN116255272A - Parallel combustion thermodynamic cycle method for improving efficiency of turbine engine - Google Patents
Parallel combustion thermodynamic cycle method for improving efficiency of turbine engine Download PDFInfo
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- CN116255272A CN116255272A CN202310177256.9A CN202310177256A CN116255272A CN 116255272 A CN116255272 A CN 116255272A CN 202310177256 A CN202310177256 A CN 202310177256A CN 116255272 A CN116255272 A CN 116255272A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
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Abstract
The invention provides a parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine, wherein the cycle consists of two single Brayton cycles with different cycle temperature increase ratios, and the parallel combustion thermodynamic cycle method is realized on the basis of two combustion chambers of an aeroengine. a- & gt, b- & gt, c- & gt, d- & gt, a- & gt, b- & gt, h- & gt, i- & gt, a respectively represent a main cycle and an outer culvert cycle formed along the flow paths of the main combustion chamber and the outer culvert combustion chamber; a- > b is an adiabatic compression process, b- > c and b- > h are isobaric endothermic processes, c- > d and h- > i are adiabatic expansion processes, and d- > a and i- > a are isobaric exothermic processes. The cyclic application process is that the working medium enters the main combustion chamber and the outer culvert combustion chamber through adiabatic compression and diversion, thereby forming high temperature and high pressure, and finally the working medium is sprayed out by the spray pipe to complete the cycle. Because the external circulation part has no limit of turbine materials on temperature, higher temperature rise can be realized, the circulation work amount is obviously increased compared with the single combustion Brayton cycle, and the oil consumption rate is obviously reduced compared with the same thrust of the afterburning Brayton cycle.
Description
Technical Field
The invention relates to the technical field of thermodynamics and power, in particular to a parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine.
Background
Starting from the 18 th century end Watt (Watt) improved steam engine, the heat engine starts to provide unprecedented huge power for the development of the industrial revolution, and from this moment, the thermodynamic cycle becomes a long-lasting research topic so far, how to make the thermodynamic cycle efficiency higher, make the work done by the cycle more and so on in the direction of continuous human research. The Carnot principle proposed by Carnot (Sadi Carnot) in 1824 is the classical theory of heat engines; the Otto (Nicolaus Auguest Otto) of De-national in 1876 is manufactured into a four-stroke gas engine by using Otto cycle, the compression ratio is about 2.5, and the thermal efficiency is 10-12%; the compression ignition Diesel engine is invented by De-national Rudorf Diesel (Rudorf Diesel) in 1897, and the Diesel cycle is also called constant pressure heating cycle and consists of two adiabatic processes, an isobaric process and an isovolumetric process; in 1926, exhaust gas turbochargers have been designed that compress the intake air using the energy of the exhaust gas, but the supercharging technology has not been popularized and popularized for many years because no well performing supercharger has been manufactured at the time. After the second world war, significant advances in refractory materials and compressors have been made with the research of exhaust gas turbines. About 1950, a supercharging method was started to be used in diesel engines. The increasing temperature increase and diffusion ratio increases the thermodynamic cycle of modern gas turbines.
Modern aero-engine belongs to gas turbine, its thermodynamic cycle in the course of working is the brayton cycle, and the working medium is passed through the adiabatic compression of compressor and heated in combustion chamber and then passed through the adiabatic expansion of turbine, and in this course the turbine is driven to do work, and self internal energy decreasingly reduces. And according to the Brabender cycle, the mode of improving the performance of the aeroengine is to improve the temperature before the turbine and the pressure ratio of the compressor as much as possible. The limitation of the turbine and the compressor in a general aeroengine causes that the temperature in the engine cannot reach the maximum temperature of ideal design, so that the cycle temperature increasing ratio is limited. However, eliminating the power rotor portion, such as a stamped engine, can cause difficulty in ground starting of the engine in the low speed region. Whereas the brayton cycle is commonly used with Afterburners (AB) in modern turbojet and turbofan engines to improve engine performance; and through development for half a century, the technology is mature, but the defects are also outstanding, the combustion in low-pressure air flow brings high heat efficiency and low oil consumption, and the size and the weight are increased. Therefore, the invention provides a novel power circulation mode, one part of working medium subjected to adiabatic compression is circulated without turbine components, the other part of working medium is circulated in a normal traditional Brayton cycle, and the two circulation modes are combined to form a novel circulation mode, so that the heating ratio is greatly improved under the condition of not reducing the pressure ratio, and the circulation work amount and efficiency are effectively improved.
Disclosure of Invention
Aiming at the defects in the background technology, the invention provides a parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine, and the circulation work amount is obviously increased compared with a single Brabender cycle, so that the thrust level of the engine is improved, the fuel consumption is reduced, and the structure is more compact.
A parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine comprises the steps that a main combustion runner working medium performs an open first Brabender cycle, and an outer culvert runner working medium performs an open second Brabender cycle;
the first brayton cycle comprises the following four processes:
process 1: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the main combustion flow path working medium is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the main combustion flow path working medium is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the main combustion flow path working medium is unchanged from the state a to the state b;
process 2: the isobaric heat absorption process is carried out in a main combustion chamber of a main combustion flow path, the main combustion flow path working medium is changed into a state c after external energy is absorbed by the state b and is converted into internal energy of the main combustion flow path working medium, at the moment, the temperature is highest in the whole first Brayton cycle, the ratio of the temperature in the state c to the temperature in the state a is the cycle heating ratio of the first Brayton cycle, and the pressure of the main combustion flow path working medium is unchanged from the state b to the state c;
process 3: the adiabatic expansion process is completed by the turbine and the tail nozzle, the main fuel runner working medium is changed into a state d after the pressure is reduced, the temperature is reduced and the speed is increased from the state c, and the entropy of the main fuel runner working medium is unchanged from the state c to the state d;
process 4: in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat and spray work to the atmosphere, so that the main fuel runner working medium changes from a state d to a state a, and the pressure of the main fuel runner working medium from the state d to the state a is unchanged;
the second brayton cycle comprises the following four processes:
process a: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the working medium of the external flow path is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the working medium of the external flow path is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the working medium of the main combustion flow path is unchanged from the state a to the state b; the cycle pressure ratio of the second Brayton cycle is the same as the cycle pressure ratio of the first Brayton cycle;
process B: the isobaric heat absorption process is carried out in an external culvert combustion chamber, and the external energy absorbed by the state b is converted into internal energy and then is changed into a state h, wherein the temperature is highest in the whole second Brabender cycle; the ratio of the temperature in the state h to the temperature in the state a is the cycle warming ratio of the second brayton cycle; the cycle temperature increase ratio of the second brayton cycle is higher than the cycle temperature increase ratio of the first brayton cycle; the temperature limit caused by the turbine material is avoided in the outer culvert flow path, so that the temperature of the outlet fuel gas of the outer culvert combustion chamber can reach higher temperature as much as possible and is obviously higher than the temperature of the mouth of the main combustion chamber;
process C: the adiabatic expansion work is completed by the culvert adjustable spray pipe, the working medium of the culvert runner is changed into a state i after the pressure of the state h is reduced, the temperature is reduced and the speed is increased, and the entropy of the working medium of the culvert runner is unchanged from the state h to the state i;
process D: and in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat, and work is sprayed out to the atmosphere, so that the working medium of the external culvert runner is changed from the state i to the state a, and the pressure of the working medium of the external culvert runner from the state i to the state a is unchanged.
As a further optimization scheme of the parallel combustion thermodynamic cycle method for improving the efficiency of the turbine engine, the heat absorption Q of the parallel combustion thermodynamic cycle in Heat absorption Q for the first brayton cycle 2 main combustor Plus the heat absorption quantity Q of the second brayton cycle process B outer combustor The calculation formula is as follows:
in the method, in the process of the invention,
c represents the air flow rate into the main combustion flow path and the external flow path, respectively p Constant pressure specific heat capacity of working medium, T b 、T c And T h The temperatures of the working medium in the state b, the state c and the state h are respectively;
heat release Q of circulation out Comprises two parts, one part is from the heat absorbed by the combustion of the fuel in the main combustion chamber, the other part is from the heat released by the combustion in the external combustion chamber, and the net work amount W is circulated net ＝Q in -Q out Therefore, the cycle thermal efficiency eta of the parallel combustion thermodynamic cycle t The formula of (2) is as follows:
wherein T is a 、T d 、T i The temperatures of the working medium in the state a, the state d and the state h are respectively.
As a further optimization scheme of the parallel combustion thermodynamic cycle method for improving the efficiency of the turbine engine, the flow distribution of the main combustion runner and the external culvert runner is realized by arranging a diversion adjusting blunt body at the outlet of the air compressor.
Compared with the prior art, the technical scheme provided by the invention has the following technical effects:
the parallel combustion thermodynamic cycle method for improving the efficiency of the turbine engine is different from the Brayton cycle which is widely applied to a single combustion chamber and an aeroengine with an afterburner at present and corresponds to a, b, c, d, a, b, c, e, f, g and a formed by broken lines of the abstract drawing, and the novel thermodynamic cycle utilizes the parallel combustion technology to be applied to the aeroengine, so that the cyclic work load is larger than that of the aeroengine with the single combustion chamber, and the fuel consumption rate is lower than that of the aeroengine with the afterburner under the same thrust. And through the blunt body of reposition of redundant personnel regulation, can be in parallelly connected burning thermodynamic cycle practical application under aeroengine different operating modes main outer culvert flow regulation, reach the effect of output maximum thrust.
Drawings
FIGS. 1 (a) and 1 (b) are schematic P-V and T-S diagrams of parallel combustion and Brayton cycles, respectively, of the present invention;
FIG. 2 is a cross-sectional view of a parallel combustion thermodynamic cycle aircraft engine configuration in which the present invention is applied to the aircraft engine;
FIG. 3 is a flow chart of the working fluid of the present invention in an aircraft engine application.
In the figure, the air compressor is 1-, the blunt body is regulated in 2-shunt, the main combustion chamber is 3-, the turbine is 4-, the 5-connotation fixed spray pipe is 6-connotation combustion chamber, and the 7-connotation adjustable spray pipe is 7-connotation.
Detailed Description
The present invention will be described in further detail with reference to the following examples, in order to make the objects, technical solutions and effects of the present invention more apparent and clear. It should be noted that the detailed description herein is for purposes of illustration only and is not intended to limit the invention.
The invention discloses a parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine, wherein a main fuel runner working medium performs an open first Brabender cycle, and an external culvert runner working medium performs an open second Brabender cycle;
the first brayton cycle comprises the following four processes:
process 1: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the main combustion flow path working medium is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the main combustion flow path working medium is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the main combustion flow path working medium is unchanged from the state a to the state b;
process 2: the isobaric heat absorption process is carried out in a main combustion chamber of a main combustion flow path, the main combustion flow path working medium is changed into a state c after external energy is absorbed by the state b and is converted into internal energy of the main combustion flow path working medium, at the moment, the temperature is highest in the whole first Brayton cycle, the ratio of the temperature in the state c to the temperature in the state a is the cycle heating ratio of the first Brayton cycle, and the pressure of the main combustion flow path working medium is unchanged from the state b to the state c;
process 3: the adiabatic expansion process is completed by the turbine and the tail nozzle, the main fuel runner working medium is changed into a state d after the pressure is reduced, the temperature is reduced and the speed is increased from the state c, and the entropy of the main fuel runner working medium is unchanged from the state c to the state d;
process 4: in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat and spray work to the atmosphere, so that the main fuel runner working medium changes from a state d to a state a, and the pressure of the main fuel runner working medium from the state d to the state a is unchanged;
the second brayton cycle comprises the following four processes:
process a: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the working medium of the external flow path is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the working medium of the external flow path is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the working medium of the main combustion flow path is unchanged from the state a to the state b; the cycle pressure ratio of the second Brayton cycle is the same as the cycle pressure ratio of the first Brayton cycle;
process B: the isobaric heat absorption process is carried out in an external culvert combustion chamber, and the external energy absorbed by the state b is converted into internal energy and then is changed into a state h, wherein the temperature is highest in the whole second Brabender cycle; the ratio of the temperature in the state h to the temperature in the state a is the cycle warming ratio of the second brayton cycle; the cycle temperature increase ratio of the second brayton cycle is higher than the cycle temperature increase ratio of the first brayton cycle; the temperature limit caused by the turbine material is avoided in the outer culvert flow path, so that the temperature of the outlet fuel gas of the outer culvert combustion chamber can reach higher temperature as much as possible and is obviously higher than the temperature of the mouth of the main combustion chamber;
process C: the adiabatic expansion work is completed by the culvert adjustable spray pipe, the working medium of the culvert runner is changed into a state i after the pressure of the state h is reduced, the temperature is reduced and the speed is increased, and the entropy of the working medium of the culvert runner is unchanged from the state h to the state i;
process D: and in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat, and work is sprayed out to the atmosphere, so that the working medium of the external culvert runner is changed from the state i to the state a, and the pressure of the working medium of the external culvert runner from the state i to the state a is unchanged.
Heat absorption quantity Q of the parallel combustion thermodynamic cycle in Heat absorption Q for the first brayton cycle 2 main combustor Plus the heat absorption quantity Q of the second brayton cycle process B outer combustor The calculation formula is as follows:
in the method, in the process of the invention,
c represents the air flow rate into the main combustion flow path and the external flow path, respectively p Constant pressure specific heat capacity of working medium, T b 、T c And T h The temperatures of the working medium in the state b, the state c and the state h are respectively;
heat release Q of circulation out Comprises two parts, one part is from the heat absorbed by the combustion of the fuel in the main combustion chamber and the other part is from the outsideHeat released by combustion in combustion chamber, circulating net work quantity W net ＝Q in -Q out Therefore, the cycle thermal efficiency eta of the parallel combustion thermodynamic cycle t The formula of (2) is as follows:
in, T a T d 、T i The temperatures of the working medium in the state a, the state d and the state h are respectively.
The flow distribution of the main combustion flow channel and the external culvert flow channel is realized by arranging a diversion adjusting blunt body at the outlet of the air compressor.
As shown in fig. 1 (a) and 1 (b), the novel thermodynamic cycle is performed in such a way that:
(1) From the cyclic process point of view:
the main combustion flow path working medium sequentially carries out adiabatic compression process (a-b), isobaric heat absorption process (b-c) and adiabatic expansion process (c)
D), isobaric exothermic process (d→a); the external flow path working medium sequentially carries out an adiabatic compression process (a-b), an isobaric heat absorption process (b-h), an adiabatic expansion work (h-i) and an isobaric heat release process (i-a) which are all four processes.
(2) From the energy conversion point of view:
the heat absorption process, namely the circulation process (b-c), is carried out in a main combustion chamber of the main combustion flow path, and the circulation process (b-h) is carried out in an outer culvert combustion chamber of the outer culvert flow path, wherein the outlet temperature of the outer culvert combustion chamber is obviously higher than that of the main combustion chamber.
The heat release process, namely the circulation processes (d-a) and (i-a), are all that the high-temperature gas sprayed by the spray pipe enters the environment to release heat.
(3) Comparison with a conventional brayton cycle:
the parallel combustion thermodynamic cycle is different from the Brayton cycle which is formed by broken lines and corresponds to a- & gtb- & gtc- & gtd and a- & gtb- & gtc- & gte- & gtf- & gtg- & gta and is widely applied to a single combustion chamber and an aircraft engine with an afterburner at present, the novel thermodynamic cycle is applied to the aircraft engine by utilizing a parallel combustion technology, so that the cyclic work load of the aircraft engine is larger than that of the aircraft engine with the single combustion chamber (the area enclosed by a solid line is obviously larger than that of the Brayton cycle with the single combustion chamber), and the fuel consumption rate is lower than that of the aircraft engine with the afterburner under the same thrust (the novel thermodynamic cycle has an average heat absorption temperature higher than that of the Brayton cycle with the afterburner).
As shown in fig. 2, in the practical application of the aeroengine, the parallel combustion cycle distributes the air flow after the adiabatic compression of the compressor to the main culvert combustion chamber through the shunt regulating blunt body, the main combustion chamber is a cyclone combustion chamber, and the culvert combustion chamber is a concave cavity combustion chamber with a support plate. In the P-V diagram, the enclosed curve enclosed by four points chid is the circulating net work quantity of the external combustion chamber which is more than that of the main combustion chamber due to higher temperature rise. And with the change of the external incoming flow Mach number and the temperature and the pressure of the aero-engine under different working conditions, the flow distribution adjusting blunt body can achieve the purpose of adjusting flow distribution through rotation, so that the component performance of the engine can be exerted as much as possible when the engine applies thermodynamic cycle under different working conditions, and the optimal application effect of the parallel combustion thermodynamic cycle is achieved.
As shown in fig. 3, which shows a cycle process of the parallel combustion thermodynamic cycle working medium in the application of an engine, the working medium is changed as follows in sequence:
(1) The working medium is subjected to adiabatic compression in the air compressor, so that the pressure is increased, the temperature is increased, and the speed is reduced;
(2) After adiabatic compression, the working medium can be distributed to a main combustion chamber and an external combustion chamber according to the state of the current engine, the two working mediums are subjected to an isobaric heat absorption process, the fuel oil is combusted in the main combustion chamber to release heat energy to heat the working medium, the temperature is increased, and the energy is converted into the internal energy of the working medium from the chemical energy in kerosene;
(3) After the working medium absorbs heat in an isobaric way, the working medium flowing out of the main combustion chamber pushes the turbine to rotate so as to drive the compressor to work, the pressure is reduced, the temperature is reduced, the speed is increased, a part of energy of the working medium is converted into mechanical energy of the turbine, and then the mechanical energy is continuously subjected to adiabatic expansion in the tail nozzle, so that the pressure is reduced, the temperature is reduced, and the speed is increased; the working medium flowing out of the culvert combustion chamber does not generate redundant functions to push the engine, and directly enters the culvert adjustable spray pipe to expand;
(4) After the working medium is subjected to adiabatic expansion in the step (3), the working medium is sprayed out from the spray pipe to enter the atmosphere for releasing heat, meanwhile, thrust is generated, the pressure of the working medium is unchanged, and the temperature and the speed are reduced.
(5) The cycle is continuously carried out from (1) to (4).
If the total amount of working medium is 1, the amount of the working medium which is split into the main combustion chamber is x, the amount of the working medium which is split into the external combustion chamber is 1-x, and the cyclic heat efficiency can be simplified as follows:
it will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the prior art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.
The foregoing is merely a preferred embodiment of the invention, and it should be noted that modifications could be made by those skilled in the art without departing from the principles of the invention, which modifications would also be considered to be within the scope of the invention.
Claims (3)
1. A parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine is characterized in that a main fuel runner working medium performs an open first Brabender cycle, and an outer culvert runner working medium performs an open second Brabender cycle;
the first brayton cycle comprises the following four processes:
process 1: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the main combustion flow path working medium is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the main combustion flow path working medium is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the main combustion flow path working medium is unchanged from the state a to the state b;
process 2: the isobaric heat absorption process is carried out in a main combustion chamber of a main combustion flow path, the main combustion flow path working medium is changed into a state c after external energy is absorbed by the state b and is converted into internal energy of the main combustion flow path working medium, at the moment, the temperature is highest in the whole first Brayton cycle, the ratio of the temperature in the state c to the temperature in the state a is the cycle heating ratio of the first Brayton cycle, and the pressure of the main combustion flow path working medium is unchanged from the state b to the state c;
process 3: the adiabatic expansion process is completed by the turbine and the tail nozzle, the main fuel runner working medium is changed into a state d after the pressure is reduced, the temperature is reduced and the speed is increased from the state c, and the entropy of the main fuel runner working medium is unchanged from the state c to the state d;
process 4: in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat and spray work to the atmosphere, so that the main fuel runner working medium changes from a state d to a state a, and the pressure of the main fuel runner working medium from the state d to the state a is unchanged;
the second brayton cycle comprises the following four processes:
process a: the adiabatic compression process is completed by the air compressor, air flow is distributed at an outlet of the air compressor to enter a main combustion flow path and an external flow path respectively, the initial state of the working medium of the external flow path is state a, at the moment, the pressure and the temperature are lowest in the whole first Brabender cycle, the working medium of the external flow path is changed into state b after the temperature is increased and the speed is reduced from the state a, the ratio of the pressure in the state b to the pressure in the state a is the cyclic pressurization ratio of the first Brabender cycle, and the entropy of the working medium of the main combustion flow path is unchanged from the state a to the state b; the cycle pressure ratio of the second Brayton cycle is the same as the cycle pressure ratio of the first Brayton cycle;
process B: the isobaric heat absorption process is carried out in an external culvert combustion chamber, and the external energy absorbed by the state b is converted into internal energy and then is changed into a state h, wherein the temperature is highest in the whole second Brabender cycle; the ratio of the temperature in the state h to the temperature in the state a is the cycle warming ratio of the second brayton cycle; the cycle temperature increase ratio of the second brayton cycle is higher than the cycle temperature increase ratio of the first brayton cycle; the temperature limit caused by the turbine material is avoided in the outer culvert flow path, so that the temperature of the outlet fuel gas of the outer culvert combustion chamber can reach higher temperature as much as possible and is obviously higher than the temperature of the mouth of the main combustion chamber;
process C: the adiabatic expansion work is completed by the culvert adjustable spray pipe, the working medium of the culvert runner is changed into a state i after the pressure of the state h is reduced, the temperature is reduced and the speed is increased, and the entropy of the working medium of the culvert runner is unchanged from the state h to the state i;
process D: and in the isobaric heat release process, high-temperature gas sprayed out of the spray pipe enters the environment to release heat, and work is sprayed out to the atmosphere, so that the working medium of the external culvert runner is changed from the state i to the state a, and the pressure of the working medium of the external culvert runner from the state i to the state a is unchanged.
2. A parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine as claimed in claim 1, wherein the heat absorption Q of the parallel combustion thermodynamic cycle in Heat absorption Q for the first brayton cycle 2 maincombustor Plus the heat absorption quantity Q of the second brayton cycle process B outercombustor The calculation formula is as follows:
in the method, in the process of the invention,
c represents the air flow rate into the main combustion flow path and the external flow path, respectively p Constant pressure specific heat capacity of working medium, T b 、T c And T h The temperatures of the working medium in the state b, the state c and the state h are respectively;
heat release Q of circulation out Comprises two parts, one part is from the heat absorbed by the combustion of the fuel in the main combustion chamber, the other part is from the heat released by the combustion in the external combustion chamber, and the net work amount W is circulated net ＝Q in -Q out Therefore, the cycle thermal efficiency eta of the parallel combustion thermodynamic cycle t The formula of (2) is as follows:
wherein T is a 、T d 、T i The temperatures of the working medium in the state a, the state d and the state h are respectively.
3. The parallel combustion thermodynamic cycle method for improving the efficiency of a turbine engine of claim 1, wherein the flow distribution of the main and the outer culvert runners is achieved by providing a split flow conditioning bluff body at the compressor outlet.
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