CN109372657B - Novel precooling air combination engine - Google Patents
Novel precooling air combination engine Download PDFInfo
- Publication number
- CN109372657B CN109372657B CN201811014133.9A CN201811014133A CN109372657B CN 109372657 B CN109372657 B CN 109372657B CN 201811014133 A CN201811014133 A CN 201811014133A CN 109372657 B CN109372657 B CN 109372657B
- Authority
- CN
- China
- Prior art keywords
- helium
- hydrogen
- air
- way
- heat exchanger
- 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.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The utility model provides a novel precooling air makes up engine, including air combustion way (1), helium cooling way (2), hydrogen energy supply way (3), through the ultra-low temperature characteristic that utilizes liquid hydrogen fuel, cool off the high temperature incoming flow air after the intake duct stagnation, and introduce helium cooling way (2) and regard as the intermediate cycle, carry out energy transfer and conversion between hydrogen energy supply way (3) and air combustion way (1), the fuel and the fuel combustion rate of cooling demand have been reduced, the concurrent heating power of heater has been reduced, the characteristics that have flight envelope large, the mode conversion is simple and fast, air precooling is efficient and the system is than impulsive height, can be as the one-level of the repeatable two-stage orbit aircraft of horizontal take-off and land and close on the high hypersonic speed platform of air and put in driving system.
Description
Technical Field
The invention relates to a novel precooled air combined engine, and belongs to the field of precooled air combined engine design.
Background
With the increasing frequency of space launching activities, the requirements on repeatable and low-cost space vehicles are more and more urgent, and the strategic position of the hypersonic aircraft in the adjacent space is also gradually paid attention. Under the background, a precooling air type combined power system introducing closed helium circulation as an intermediate medium becomes one of research hotspots in the field of hypersonic speeds at home and abroad due to the advantages of large working envelope, simple mode conversion, high component sharing degree and the like. The existing world is the SABRE scheme proposed by REL corporation of british, which includes two working modes of air suction mode and pure rocket mode, and introduces closed helium cycle as medium to absorb heat of incoming air, and uses low-temperature hydrogen fuel to absorb residual heat of helium circuit to make its flow path closed, and when the heat absorbed by helium from air is insufficient, the SABRE scheme specially uses heater to supplement heat for helium. The major deficiencies of the SABRE protocol: the air precooling efficiency of the scheme is low, so that the fuel consumption rate of the system is high, and the specific impulse performance of the system is low; in the air suction mode, the wall surface of the combustion chamber is cooled by air and hydrogen, and a part of fuel cooling capacity needs to be sacrificed, so that extra fuel consumption is caused, and the specific impulse of the system is further reduced; the design requirements for each part are high, a plurality of key technologies which are difficult to realize are involved, and the current engineering feasibility of the system scheme is low.
Disclosure of Invention
The technical problem solved by the invention is as follows: aiming at the problems that the fuel consumption rate is too high, the specific impulse performance of a system is lower and the high performance of the system is difficult to realize in the prior art in the engine precooling technology, a novel precooled air combined engine is provided.
The technical scheme for solving the technical problems is as follows:
the utility model provides a novel precooling air combination engine, includes air combustion way, helium cooling way, hydrogen energy supply way, air combustion way receives the outside air, the helium cooling way cools off this way air, and hydrogen heats up in the way to the hydrogen energy supply simultaneously, hydrogen energy supply way is to air combustion way output back hydrogen that heaies up, makes in the way air of hydrogen and air combustion way that heaies up converge in the output and burn the energy supply.
The hydrogen combustion auxiliary path is characterized by further comprising an air combustion auxiliary path, if the air inflow of the air combustion path is larger than the maximum allowable air inlet threshold, part of air exceeding the maximum allowable air inlet threshold is sent into the air combustion auxiliary path, and the air combustion auxiliary path and the heated hydrogen output by the hydrogen supply path are converged at the output end of the air combustion auxiliary path to supply auxiliary power.
The air combustion way includes intake duct, air compressor, outer combustion chamber of containing, outer spray tube of containing, integrated heater, and the air is gathered by the intake duct and is carried out two way outputs, exports all the way to outer combustion chamber of containing and hydrogen supply way provides hydrogen and joins and burns, carries out the precooling via the helium cooling way all the way after, again through the air compressor pressure boost and through outer spray tube entering integrated heater of containing, join and the abundant burning with the hydrogen that the hydrogen supply way provided.
The helium cooling circuit comprises a helium filling pipe, a precooler, a helium turbine, a first helium compressor, a second helium compressor, a first hydrogen helium heat exchanger and a second helium heat exchanger, wherein the helium filling pipe respectively fills thermal circulating helium to the helium turbine and the second helium heat exchanger, and the helium cooling circuit comprises:
the helium turbine cools and reduces the temperature and pressure of thermal cycle helium, the helium after cooling and reducing the pressure is sent to the first hydrogen helium heat exchanger, the first hydrogen helium heat exchanger heats the hydrogen in the hydrogen energy supply path by using the helium after cooling and reducing the pressure and sends the helium after cooling to the first helium compressor, and the first helium compressor supplements the pressure of the helium after cooling and sends the helium after cooling to the precooler to cool air in the air combustion path;
the second helium heat exchanger utilizes thermal cycle helium to heat hydrogen in the hydrogen supply path and sends cooled helium to the second helium compressor, and the second helium compressor supplements pressure to the cooled helium and sends the supplemented helium to the precooler to cool air in the air combustion auxiliary path.
The hydrogen energy supply circuit comprises a fuel storage tank, a hydrogen pump and a hydrogen turbine, wherein:
the fuel storage tank sends the liquid hydrogen to the hydrogen pump, the hydrogen pump boosts the liquid hydrogen and sends the boosted liquid hydrogen to the first hydrogen helium heat exchanger to absorb heat, the hydrogen turbine cools the hydrogen after temperature rise and sends the hydrogen to the second helium heat exchanger to absorb heat, and the hydrogen after temperature rise is respectively sent to the integrated heater and the outer culvert combustion chamber.
The temperature of the thermal cycle helium primarily filled by the helium filling pipe is 1000K, and the pressure is 20 Mpa.
And after the helium gas in the helium gas cooling circuit exchanges heat through the first hydrogen-helium heat exchanger, the temperature is 600K.
And after the hydrogen in the hydrogen energy supply path exchanges heat through the first hydrogen-helium heat exchanger, the temperature is 600K.
Preferably, the temperature of the helium gas in the helium gas cooling circuit is 350K after heat exchange by the second hydrogen-helium heat exchanger.
Further, after the hydrogen in the hydrogen supply path exchanges heat through the second hydrogen-helium heat exchanger, the temperature is 300K.
Compared with the prior art, the invention has the advantages that:
the invention provides a novel precooling air combined engine, which utilizes the ultralow temperature characteristic of liquid hydrogen fuel to cool high-temperature incoming flow air which is stagnated by an air inlet channel, introduces a helium path as intermediate circulation to carry out energy transfer and conversion between the hydrogen path and the air path, adopts a circulation scheme of flow division and heat regeneration, utilizes a thrust chamber to supplement a part of heat for the helium path, adopts a circulation scheme of graded cooling in the hydrogen path, enters a hydrogen turbine to expand and do work after absorbing waste heat from helium in a hydrogen-helium heat exchanger, and enters another group of hydrogen-helium heat exchanger to absorb the waste heat of the helium path after reducing the temperature, so that the hydrogen flow consumed in the cooling process is obviously reduced, the extra fuel waste caused by cooling the thrust chamber by fuel is avoided, the heat of the thrust chamber can be utilized to supplement heat for the helium path, the specific impulse performance of a system is improved, and the fuel consumption rate is reduced.
Drawings
FIG. 1 is a circuit diagram of an engine system architecture provided by the present invention;
FIG. 2 is a block diagram of an engine system provided by the present invention;
FIG. 3 is a schematic diagram of an air combustion circuit provided by the present invention;
FIG. 4 is a schematic diagram of a helium cooling circuit provided by the present invention;
FIG. 5 is a schematic diagram of a hydrogen gas supply circuit provided by the present invention;
Detailed Description
A novel precooled air combined engine is shown in figure 1 and comprises an air combustion path 1, a helium cooling path 2 and a hydrogen energy supply path 3, wherein heat in high-temperature incoming flow air after stagnation of an air inlet channel is absorbed by the ultralow-temperature characteristic of liquid hydrogen fuel, the helium cooling path 2 is introduced to serve as intermediate circulation, and energy transfer and conversion between the air combustion path 1 and the hydrogen energy supply path 3 are carried out. It is characterized in that: the helium cooling circuit 2 adopts a split-flow regenerative cycle scheme, and a thrust chamber is utilized to supplement a part of heat for the helium cooling circuit 2; the hydrogen energy supply path 3 adopts a circulation scheme of graded cooling, hydrogen enters a hydrogen turbine to do work after absorbing waste heat from helium in a heat exchanger, and enters another heat exchanger to absorb the waste heat of a helium path after the temperature is reduced.
The air combustion path 1 comprises an air inlet channel 11, an air compressor 14, a bypass combustion chamber 15, a bypass spray pipe 16 and an integrated heater 17, wherein the air inlet channel 11 is used for capturing incoming air and pressurizing the incoming air by using a shock wave system. The precooler is located after the inlet and functions to cool the incoming air with low temperature helium. An air compressor 14 is located downstream of the precooler and functions to boost the pressure of the precooled air. The integrated heater 17 can be functionally divided into a pre-combustion module, a heat exchange module and a thrust chamber module, and is used for forming oxygen-enriched high-temperature fuel gas, supplementing heat for helium when the helium absorbs insufficient heat in the air inlet channel 11, maintaining the helium cooling circuit 2 to be circularly closed, and enabling the oxygen-enriched fuel gas after heat supplementation to be more fully combusted with fuel in the thrust chamber module so as to provide energy for an engine. When the air quantity captured by the air inlet 11 is larger than the air quantity required by the air compressor, the redundant air and fuel are combusted in the bypass combustion chamber 15, high-temperature fuel gas is formed and expands in the bypass nozzle 16, and a part of thrust is provided for the system.
The helium cooling path 2 comprises a helium filling pipe 4, a precooler 5, a helium turbine 21, a first helium compressor 22, a second helium compressor 24, a first hydrogen helium heat exchanger 26 and a second hydrogen helium heat exchanger 27, wherein the helium filling pipe 4 respectively fills heat circulation helium into the helium turbine 21 and the second hydrogen helium heat exchanger 27, one path exchanges heat with the hydrogen gas energy supply path 3 through the first hydrogen helium heat exchanger 26, the cooled and depressurized helium gas is used for heating the hydrogen gas in the hydrogen gas energy supply path 3 and sending the cooled helium gas to the first helium compressor 22, and the first helium compressor 22 performs pressure compensation on the cooled helium gas and then sends the pressure compensated helium gas to the precooler 5 to cool one path of air in the air combustion path 1; the other path of helium is used for heating the hydrogen in the hydrogen supply path 3 and sending the cooled helium to the second helium compressor 24, and then the second helium compressor 24 supplements pressure to the cooled helium and sends the supplemented helium to the precooler 5 to cool the air in the same path of the air combustion path 1.
The hydrogen energy supply path 3 comprises a fuel storage tank 31, a hydrogen pump 32 and a hydrogen turbine 33, the fuel storage tank 31 sends liquid hydrogen into the hydrogen pump 32, the hydrogen pump 32 boosts the liquid hydrogen and sends the boosted liquid hydrogen to the first hydrogen-helium heat exchanger 26, the helium in the helium cooling path 2 is cooled through the first hydrogen-helium heat exchanger 26 and sent to the hydrogen turbine 33 after being heated, the hydrogen turbine 33 cools the hydrogen after being heated and sends the hydrogen after being cooled to the second hydrogen-helium heat exchanger 27, the second hydrogen-helium heat exchanger 27 cools the helium in the helium cooling path 2 and sends the hydrogen after being heated to the integrated heater 17 and the outer culvert combustion chamber 15 respectively to be merged with air for combustion.
The following is further illustrated with reference to specific examples:
a novel precooling air combined engine is set, wherein the novel precooling air combined engine comprises an air combustion path 1, a helium cooling path 2, a hydrogen energy supply path 3, a high-temperature precooler 12, a low-temperature precooler 13, a first regulating valve 28 and a second regulating valve 29;
the air combustion path 1 comprises an air inlet channel 11, an air compressor 14, a culvert combustion chamber 15, a culvert spray pipe 16 and an integrated heater 17;
the helium cooling circuit 2 comprises a helium turbine 21, a first helium compressor 22, a second helium compressor 23, a third helium compressor 24, a first hydrogen helium heat exchanger 26, a third helium heat exchanger 29 and a second hydrogen helium heat exchanger 27;
the hydrogen energy supply path 3 comprises a fuel storage tank 31, a hydrogen pump 32, a first hydrogen turbine 33, a second hydrogen turbine 34 and a third hydrogen turbine 35, wherein the connection relation and the working flow of the engine are as follows:
the helium absorbs heat from the air in the precooler and supplements the heat for the helium circuit at the integrated heater 17 using the fuel gas when required. The helium absorbing enough heat enters the helium turbine 21 to expand and do work, and a part of the heat is converted into mechanical work to drive the air compressor 14 to rotate. Helium is divided into two paths at the outlet of the helium turbine 21, one path directly enters the first hydrogen helium heat exchanger 26 to exchange heat with low-temperature hydrogen, then enters the first helium compressor 22 for pressure compensation, is used as cold coal to enter the third helium heat exchanger 29 for heat exchange after being pressurized, and finally sequentially enters the high-temperature precooler 12 and the integrated heater 17 to absorb heat, so that the flow path is closed; the other path is cooled by low-temperature helium in a third helium-helium heat exchanger 29, enters a second helium compressor 23 for pressure compensation, and finally sequentially enters a low-temperature precooler 13, a high-temperature precooler 12 and an integrated heater 17 for heat absorption to complete the flow path closure.
From the outlet of the heater, part of helium enters a second hydrogen helium heat exchanger 27 to exchange heat with hydrogen, after heat exchange, the third helium compressor 24 with very small pressure ratio is used for supplementing pressure to the helium, and finally, the helium is merged with helium at the outlet of the second helium compressor 23 and enters the low-temperature precooler 13 to cool air through a second regulating valve 29. In the invention, helium is used as a cooling medium for the throat wall surface of the thrust chamber, part of helium is led into a cooling channel on the throat wall surface of the thrust chamber from the outlet on the cold flow side of the third helium heat exchanger 29, and finally is merged with helium from a heater before the inlet of the helium turbine 21. And the flow control valve is used for realizing flow distribution and flow control at the corresponding node.
The hydrogen energy supply path 3 comprises a fuel storage tank 31, a hydrogen pump 32, a first hydrogen turbine 33, a second hydrogen turbine 34 and a third hydrogen turbine 35, wherein hydrogen is pressurized at the outlet of the storage tank through the hydrogen pump, enters the first hydrogen helium heat exchanger 26 to absorb a part of waste heat of a helium path to become high-temperature high-pressure hydrogen with work-applying capacity, sequentially enters the first hydrogen turbine 33, the second hydrogen turbine 34 and the third hydrogen turbine 35 to expand and work to drive the helium compressor and the hydrogen pump, has cooling capacity again after temperature reduction after expansion, enters the second hydrogen helium heat exchanger 27 to absorb another part of waste heat from the helium path, and finally is divided into three paths which respectively enter an outer culvert combustion chamber, a pre-combustion module of the integrated heater 17 and a thrust chamber module.
The new engine system is shown in fig. 2, and includes an air combustion path 1, a helium cooling path 2, a hydrogen energy supply path 3, a high-temperature precooler 12, a low-temperature precooler 13, a first hydrogen-helium heat exchanger 26, a second hydrogen-helium heat exchanger 27, a first regulating valve 28, and a second regulating valve 29, where the helium cooling path 2 cools combustion air provided by the air combustion path 1 through the high-temperature precooler 12 and the low-temperature precooler 13, and controls the on-off states of the high-temperature precooler 12 and the low-temperature precooler 13 through the first regulating valve 28 and the second regulating valve 29, and absorbs heat from a gas to be combusted provided by the hydrogen energy supply path 3, and the gas to be combusted and the combustion air are combusted at an output end of the air combustion path 1 to provide heat for the engine, where:
as shown in fig. 3, the air combustion path 1 includes an air inlet 11, an air compressor 14, a bypass combustion chamber 15, a bypass nozzle 16, and an integrated heater 17, air is sent from the air inlet 11 to the air compressor 14 connected to the output end of the air inlet 11, a high-temperature precooler 12 and a low-temperature precooler 13 are disposed between the air inlet 11 and the air compressor 14, if the air intake amount is lower than the air intake flow threshold of the air compressor 14, all air is cooled by the high-temperature precooler 12 and the low-temperature precooler 13, and the cooled air is pressurized by the air compressor 14 to form oxygen-enriched fuel gas to enter the integrated heater 17; if the air inlet quantity is higher than the air inlet flow threshold value of the air compressor 14, redundant air enters the bypass combustion chamber 15 connected with the output end of the air inlet 11 from the air inlet 11 to be fully combusted, and additional thrust is provided by a bypass nozzle 16 connected with the output end of the bypass combustion chamber 15.
As shown in fig. 4, the helium cooling circuit 2 includes a helium turbine 21, a first helium compressor 22, a second helium compressor 23, a third helium compressor 24, and an output end of an external filler is respectively connected to input ends of the helium turbine 21 and the second helium hydrogen heat exchanger 27, and high-temperature and high-pressure helium gas is respectively sent to the helium turbine 21 and the second helium hydrogen heat exchanger 27 through the external filler, wherein:
the second helium hydrogen heat exchanger 27 receives high-temperature high-pressure helium gas sent by an external filling device to exchange heat with a hydrogen path for cooling, and sends the cooled helium gas to a third helium compressor 24 connected with the output end of the second helium hydrogen heat exchanger 27 for pressure compensation, and the pressure compensated helium gas is converged with pressure compensated helium gas output by the second helium compressor 23 and sequentially sent to the low-temperature precooler 13 and the high-temperature precooler 12 for air path cooling.
The helium turbine 21 receives high-temperature and high-pressure helium gas sent by an external filling device to perform expansion work and respectively sends the high-temperature and high-pressure helium gas to a first hydrogen helium heat exchanger 26 and a third hydrogen helium heat exchanger 29 which are connected with the output end of the helium turbine 21; the input end of the first hydrogen helium heat exchanger 26 receives the expanded working medium-pressure helium gas, and after the helium gas exchanges heat with a hydrogen path and is cooled, the low-temperature helium gas is sent into a first helium compressor 22 connected with the output end of the first hydrogen helium heat exchanger 26 for pressure compensation, the helium gas after pressure compensation passes through a third helium heat exchanger 29 connected with the output end of the first helium compressor 22, the third helium heat exchanger 29 receives the helium gas after pressure compensation for heat exchange and temperature rise, and the helium gas after temperature rise is divided into two paths, wherein one path is sent into the input end of a cooling thrust chamber 17 connected with the output end of the third helium heat exchanger 29, and the other path is sent into a first regulating valve 28 and then enters a high-temperature precooler 12 for cooling the air path through the first regulating valve 28;
the third helium heat exchanger 29 receives the expanded working medium-pressure helium gas, then sends the expanded working medium-pressure helium gas to the second helium compressor 23 connected with the output end of the third helium heat exchanger 29 for pressure compensation, the second helium compressor 23 sends the pressure-compensated helium gas to the second regulating valve 29 connected with the output end of the second helium compressor 23, the pressure-compensated helium gas sent by the third helium compressor 24 is converged and sent to the low-temperature precooler 13 connected with the second regulating valve 29 together for cooling the air, the cooled helium gas enters the high-temperature precooler 12 after the helium gas from the first regulating valve 28 is converged in the low-temperature precooler 13, and then enters the integrated heater 17 for heating to realize closed cycle.
As shown in fig. 5, the hydrogen gas supply path 3 includes a fuel storage tank 31, a hydrogen pump 32, a first hydrogen turbine 33, a second hydrogen turbine 34, and a third hydrogen turbine 35, an output end of the fuel storage tank 31 for storing hydrogen gas is connected to an input end of the hydrogen pump 32, the hydrogen gas is pressurized by the hydrogen pump 32 and then sent to the first hydrogen helium heat exchanger 26 connected to the output end of the hydrogen pump 32 to absorb heat in the helium path, the hydrogen gas after temperature rise sequentially passes through the first hydrogen turbine 33, the second hydrogen turbine 34, and the third hydrogen turbine 35 connected to the output end of the first hydrogen helium heat exchanger 26 to perform expansion work and then cool down, the hydrogen gas after temperature decrease absorbs heat in the helium path through the second hydrogen helium heat exchanger 27 connected to the output end of the third hydrogen turbine 35, and then enters the outer bypass combustion chamber 15 and the integrated heater 17 of the air path through an output end of the second hydrogen helium heat exchanger 27.
The black solid point on the upper left of the second hydrogen helium heat exchanger 27 is used as an initial node, the helium working mode in the above description is subjected to simple flow path schematic, each path of helium is required to return to the initial point again after working, and closed circulation is realized:
1. begin → 21 → 25 → 22 → 26 → 28 → 12 → 17 heating module → end
2. Begin → 21 → 25 → 22 → 26 → 17 throat → end
3. Begin → 21 → 26 → 23 → 29 → 13 → 12 → 17 heating module → end
4. Begin → 27 → 24 → 29 → 13 → 12 → 17 heating module → end
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A novel precooling air combination engine is characterized in that: including air combustion way (1), helium cooling way (2), hydrogen energy supply way (3), outside air is received in air combustion way (1), helium cooling way (2) cools off air combustion way (1) air, and hydrogen heaies up in hydrogen energy supply way (3) simultaneously, hydrogen energy supply way (3) to air combustion way (1) output intensification back hydrogen, make intensification back hydrogen and air combustion way (1) in the output join and burn the energy supply, and helium cooling way (2) carry out the thermal cycle through dividing the reposition of redundant personnel backheat to utilize the thrust chamber to supply the heat for helium cooling way (2).
2. The novel pre-cooled air combined engine of claim 1, characterized in that: the auxiliary air combustion system is characterized by further comprising an air combustion auxiliary path (6), if the air inflow of the air combustion path (1) is larger than the maximum allowable air inlet threshold, part of air exceeding the maximum allowable air inlet threshold is sent into the air combustion auxiliary path (6), and the air combustion auxiliary path and the hydrogen output by the hydrogen energy supply path (3) after temperature rise are converged at the output end of the air combustion auxiliary path (6) for auxiliary energy supply.
3. The novel precooled air combined engine as recited in claim 1 or claim 2, wherein: air combustion way (1) is including intake duct (11), air compressor (14), outer combustion chamber (15), outer spray tube (16) of containing, integration heater (17), the air is gathered by intake duct (11) and is carried out two way outputs, export all the way to outer combustion chamber (15) and hydrogen that hydrogen energy supply way (3) provided and join and burn, carry out the precooling back via helium cooling way (2) all the way, again through air compressor (14) pressure boost and through outer spray tube (16) entering integration heater (17), join and fully burn with the hydrogen that hydrogen energy supply way (3) provided.
4. The novel pre-cooled air combined engine of claim 3, characterized in that: the helium cooling circuit (2) comprises a helium filling pipe (4), a precooler (5), a helium turbine (21), a first helium compressor (22), a second helium compressor (24), a first hydrogen helium heat exchanger (26) and a second hydrogen helium heat exchanger (27), wherein the helium filling pipe (4) respectively fills thermal cycle helium to the helium turbine (21) and the second hydrogen helium heat exchanger (27), and the helium cooling circuit comprises:
the helium turbine (21) cools and depressurizes the thermal cycle helium, the helium after cooling and depressurization is sent to the first hydrogen helium heat exchanger (26), the first hydrogen helium heat exchanger (26) heats the hydrogen in the hydrogen energy supply path (3) by using the helium after cooling and depressurization and sends the helium after cooling to the first helium compressor (22), and the first helium compressor (22) supplements the pressure to the helium after cooling and sends the helium to the precooler (5) to cool the air in the air combustion path (1);
the second helium heat exchanger (27) heats the hydrogen in the hydrogen supply path (3) by using the thermal circulation helium gas and sends the cooled helium gas to the second helium compressor (24), and the second helium compressor (24) supplements the pressure of the cooled helium gas and sends the supplemented helium gas to the precooler (5) to cool the air in the air combustion auxiliary path (6).
5. The novel pre-cooled air combined engine of claim 4, characterized in that: the hydrogen gas supply path (3) includes a fuel tank (31), a hydrogen pump (32), and a hydrogen turbine (33), wherein:
the fuel storage tank (31) sends liquid hydrogen to the hydrogen pump (32), the hydrogen pump (32) boosts the liquid hydrogen and sends the boosted liquid hydrogen to the first hydrogen-helium heat exchanger (26) for heat absorption, the hydrogen turbine (33) cools the hydrogen after temperature rise and sends the hydrogen into the second hydrogen-helium heat exchanger (27) for heat absorption, and the hydrogen after temperature rise is respectively sent to the integrated heater (17) and the outer culvert combustion chamber (15).
6. The novel pre-cooled air combined engine of claim 4, characterized in that: the temperature of the thermal cycle helium which is filled for the first time by the helium filling pipe (4) is 1000K, and the pressure is 20 Mpa.
7. The novel pre-cooled air combined engine of claim 4, characterized in that: and the temperature of helium in the helium cooling circuit (2) is 600K after heat exchange through the first hydrogen-helium heat exchanger (26).
8. The novel pre-cooled air combined engine of claim 4, characterized in that:
and after the hydrogen in the hydrogen energy supply path (3) exchanges heat through the first hydrogen helium heat exchanger (26), the temperature is 600K.
9. The novel pre-cooled air combined engine of claim 7, characterized in that: and the temperature of helium in the helium cooling circuit (2) is 350K after heat exchange through the second hydrogen helium heat exchanger (27).
10. The new pre-cooled combined air engine of claim 8, wherein: and after the hydrogen in the hydrogen energy supply path (3) exchanges heat through the second hydrogen helium heat exchanger (27), the temperature is 300K.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811014133.9A CN109372657B (en) | 2018-08-31 | 2018-08-31 | Novel precooling air combination engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811014133.9A CN109372657B (en) | 2018-08-31 | 2018-08-31 | Novel precooling air combination engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109372657A CN109372657A (en) | 2019-02-22 |
| CN109372657B true CN109372657B (en) | 2021-09-07 |
Family
ID=65404770
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811014133.9A Active CN109372657B (en) | 2018-08-31 | 2018-08-31 | Novel precooling air combination engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109372657B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109989833A (en) * | 2019-04-24 | 2019-07-09 | 北京航空航天大学 | A kind of integrated thermal management system for hypersonic aircraft or engine |
| CN109989832A (en) * | 2019-04-24 | 2019-07-09 | 北京航空航天大学 | A kind of expansion pre-cooling cycle system for aerospace engine |
| CN110886627B (en) * | 2019-10-30 | 2022-07-29 | 北京动力机械研究所 | Integrated casing for combined engine |
| CN116480488A (en) * | 2023-06-19 | 2023-07-25 | 西安航天动力研究所 | Self-adaptive starting afterburning cycle engine system and starting method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2240815B (en) * | 1983-12-23 | 1991-12-18 | Alan Bond | Improvements in aerospace propulsion |
| RU2158839C2 (en) * | 1999-01-21 | 2000-11-10 | Открытое акционерное общество "НПО Энергомаш им. акад. В.П. Глушко" | Liquid-propellant rocket reheat engine |
| US11162424B2 (en) * | 2013-10-11 | 2021-11-02 | Reaction Engines Ltd | Heat exchangers |
| GB2519152B (en) * | 2013-10-11 | 2016-09-07 | Reaction Engines Ltd | Engine |
| CN107989699B (en) * | 2017-11-27 | 2019-09-27 | 北京航空航天大学 | Aircraft propulsion is combined in pre-cooling by force for punching press-based on double fuel Compound cooling |
-
2018
- 2018-08-31 CN CN201811014133.9A patent/CN109372657B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109372657A (en) | 2019-02-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109372657B (en) | Novel precooling air combination engine | |
| CN112325497B (en) | Liquefied carbon dioxide energy storage system and application thereof | |
| CN107630726A (en) | A kind of multipotency hybrid power system and method based on supercritical carbon dioxide circulation | |
| CN110887278B (en) | Energy self-sufficient carbon dioxide combined cooling heating and power system for low-grade heat source | |
| CN101280723B (en) | Method and device for reutilization of natural gas pipe network pressure energy in gas turbine working domain | |
| CN112377324A (en) | Active cooling and combustion decoupling system of scramjet engine | |
| CN111102025B (en) | Supercritical carbon dioxide circulating power generation system suitable for regenerative cooling detonation combustion chamber | |
| CN111306842A (en) | Variable working condition multi-energy combined supply system and method suitable for different seasons | |
| CN206582068U (en) | A kind of non-afterburning compressed air electricity generation system of photo-thermal combined type | |
| CN114198170A (en) | Carbon dioxide energy storage system based on double heat storage loops and working method thereof | |
| CN106704126B (en) | Based on compressed supercritical CO 2 Tower type solar thermal power generation system with gas energy storage function | |
| WO2023193486A1 (en) | Normal-temperature liquid compressed carbon dioxide mixed working fluid energy storage system and method | |
| CN105545486A (en) | Power generating system and method of gas turbine | |
| CN105715518A (en) | Heating-electric-cooling tri generation device with cold supply in summer and heat supply in winter and method | |
| CN112412561B (en) | Coupling control method for compressed air energy storage system and thermal power plant control system | |
| CN108612571A (en) | A kind of supercritical carbon dioxide Brayton cycle working medium regulating system and method | |
| CN110159380B (en) | Single-tank closed-type circulating energy storage power generation system | |
| CN109974323B (en) | Combined cooling heating and power circulation method and system with jet flow cooling device | |
| CN113187680B (en) | Photovoltaic power generation system with electrothermal energy storage function and operation method | |
| CN114198173A (en) | Full-backheating Brayton cycle and absorption refrigeration integrated electricity-cold combined supply system | |
| CN117052494A (en) | Multistage steady voltage cave formula adiabatic compressed air energy storage power station system | |
| CN212538358U (en) | Variable working condition multi-energy combined supply system suitable for different seasons | |
| CN205349530U (en) | Gas turbine generating system | |
| CN214660402U (en) | Supercritical CO with electric heat energy storage2Brayton cycle power generation system | |
| CN113062847B (en) | Multi-source heat accumulating type compressed air energy storage comprehensive utilization system and method |
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 |