CN113864083A - Novel variable-cycle gas turbine engine - Google Patents
Novel variable-cycle gas turbine engine Download PDFInfo
- Publication number
- CN113864083A CN113864083A CN202111187082.1A CN202111187082A CN113864083A CN 113864083 A CN113864083 A CN 113864083A CN 202111187082 A CN202111187082 A CN 202111187082A CN 113864083 A CN113864083 A CN 113864083A
- Authority
- CN
- China
- Prior art keywords
- gas turbine
- culvert
- turbine engine
- variable
- fan
- 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.)
- Pending
Links
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 19
- 230000004323 axial length Effects 0.000 claims description 3
- 238000002347 injection Methods 0.000 abstract description 3
- 239000007924 injection Substances 0.000 abstract description 3
- 230000007246 mechanism Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- 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
- F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses a novel variable-cycle gas turbine engine, and belongs to the technical field of gas turbine engines. The variable-cycle gas turbine engine adopts a single-rotor gas turbine to drive a high-pressure compressor and a differential planetary gear reducer, the differential planetary gear reducer drives a variable-angle fan and a supercharger, a duct injection valve is used for controlling the trend of an airflow path, and the variable-cycle gas turbine engine adopts a single-rotor mode to replace the traditional multi-rotor variable-cycle gas turbine engine, simplifies the support of the turbofan engine and reduces the complexity of a rotor structure system, reduces the design difficulty of an engine structure, enables the gas turbine engine to have more cycle modes, and is more suitable for complex flight states.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to a novel variable-cycle gas turbine engine.
Background
The operating modes of the turbine engine are: the rotating turbine and the compressor/fan are connected on the same shaft, a heat source is arranged between the turbine and the compressor/fan, air is continuously sucked into the compressor, compressed air enters the combustion chamber to be injected and combusted into high-temperature gas, then the high-temperature gas enters the turbine to perform expansion work, and the expansion work is transmitted to the compressor through the transmission shaft, so that the continuous work of the engine is realized. The existing variable-cycle gas turbine engine also operates according to the mode, only the structural form is changed newly, the specific structure of the Falde fan is adopted to connect the blade tips of the traditional fan into a blade ring structure, the Falde fan is mounted on the blade ring, the design is developed by matching with various bypass adjusting mechanisms, wherein the structural form of the fan, the blade ring and the Falde fan converts the traditional form of flow distribution depending on pneumatic matching into a form of flow distribution according to geometry, and the trend of air flow is restrained by opening and closing the bypass adjusting mechanisms, so that the variable bypass ratio and the variable-cycle working mode are realized.
The existing structural form of the fan, the blade ring and the Falde fan causes large stress of the blade root of the fan, and has difficulty in design and manufacture, and the air flow distribution of the fan is influenced by a geometric structure, so that the variety of the formed bypass ratio is not large, and secondly, the existing variable cycle engine adopts a multi-rotor structure, so that the structure is complex and the difficulty in engineering realization is increased.
Disclosure of Invention
It is an object of the present invention to provide a new variable cycle gas turbine engine to address at least one of the problems and deficiencies set forth in the above background.
According to one aspect of the invention, a novel variable-cycle gas turbine engine is provided, and the novel variable-cycle gas turbine engine comprises an angle-adjustable front fan, an angle-adjustable medium-pressure fan, a differential planetary reducer and a gas turbine shaft, and is characterized in that the differential planetary reducer comprises a sun gear, a planetary gear, a planet carrier and a ring gear, the sun gear is coaxially and fixedly connected with the gas turbine shaft, the planet carrier is in driving connection with the angle-adjustable front fan, and the ring gear is in driving connection with the angle-adjustable medium-pressure fan.
Further, still include three airflow channel in outer culvert, well culvert and the connotation, the position that is close to adjustable angle middling pressure fan between outer culvert and the well culvert is provided with preceding variable area culvert ejector for adjust the air intake flow ratio of outer culvert and well culvert, be close to the connotation rear end between well culvert and the connotation and be provided with back variable area culvert ejector for adjust the export gas flow ratio of well culvert and connotation.
Further, the blade tip of the angle-adjustable front fan is close to the outer side of the culvert.
Further, the blade tip of the angle-adjustable medium-pressure fan is close to the outer side of the culvert.
Further, the differential planetary reducer is arranged between the angle-adjustable front fan and the angle-adjustable medium-pressure fan.
Furthermore, the power input end of the sun gear is fixedly welded with the gas turbine shaft, or the power input end of the sun gear and the gas turbine shaft are integrally formed.
Further, a plurality of said planet gears are arranged in one or more ring gears for planetary rotation about one or more sun gears, the plurality of planet gears collectively driving a planet carrier.
Further, the planet gears are all equal in diameter and axial length.
Compared with the prior art, the invention has the beneficial effects that:
the gas turbine drives the high-pressure compressor and the differential planetary reducer through a gas turbine shaft, and drives the angle-adjustable front fan and the angle-adjustable medium-pressure fan through the output of the differential planetary reducer; three airflow channels of an outer culvert, a middle culvert and an inner culvert are formed through different airflow directions. The adjustment of the bypass ratio in a large range can be realized by adjusting the opening and closing of the bypass adjusting mechanism, namely the front variable-area bypass ejector and the rear variable-area bypass ejector, and synchronously adjusting the angles of the angle-adjustable front fan and the angle-adjustable medium-pressure fan.
The invention adopts a single-rotor gas turbine to drive a high-pressure compressor and a differential planetary reducer, the differential planetary reducer drives a variable-angle fan and a supercharger, and a duct injection valve is used for controlling the trend of an airflow path, so that a novel variable-cycle gas turbine engine adopting a single-rotor mode is formed, the novel variable-cycle gas turbine engine replaces the traditional multi-rotor variable-cycle gas turbine engine, the turbofan engine support is simplified, the complexity of a rotor structure system is reduced, the design difficulty of an engine structure is reduced, the novel gas turbine engine has more cycle modes, is more suitable for a complex flight state, and can provide power for a modern novel multifunctional task aircraft.
Drawings
In order to facilitate understanding for those skilled in the art, the present invention will be further described with reference to the accompanying drawings.
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of a differential planetary gearbox.
In the figure: 1. the angle of the front fan can be adjusted; 2. an angle-adjustable medium-pressure fan; 3. a high pressure compressor; 4. a combustion chamber; 5. a gas turbine; 6. carrying out external culvert; 7. carrying out intermediate culvert; 8. connotation; 9. a front variable area ducted ejector; 10. a rear variable area ducted ejector; 11. a differential planetary reducer; 12. a gas turbine shaft; 13. a sun gear; 14. a planetary gear; 15. a planet carrier; 16. a ring gear.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention are further described in detail below by way of examples with reference to the accompanying drawings. In the specification, the same or similar reference numerals denote the same or similar components. The following description of the embodiments of the present invention with reference to the drawings is intended to be illustrative of the general inventive concepts of the present invention and should not be construed as limiting the novel variable cycle gas turbine engine of the present invention.
Furthermore, in the following detailed description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the embodiments of the disclosure. It may be evident, however, that one or more embodiments may be practiced without these specific details. In other instances, well-known structures and devices are shown in schematic form in order to simplify the drawing.
According to a general technical concept of the present invention, as shown in fig. 1-2, a novel variable cycle gas turbine engine is provided, which mainly comprises an angle-adjustable front fan 1, an angle-adjustable medium pressure fan 2, a high pressure compressor 3, a combustion chamber 4, a gas turbine 5, a differential planetary reducer 11 and a gas turbine shaft 12, wherein the differential planetary reducer 11 comprises a sun gear 13, a planetary gear 14, a planet carrier 15 and a ring gear 16, the sun gear is a power input end, the planet carrier 15 and the ring gear 16 are power output ends, the sun gear 13 is coaxially and fixedly connected with the gas turbine shaft 12, the planet carrier 15 is in driving connection with the angle-adjustable front fan 1, the ring gear 16 is in driving connection with the angle-adjustable medium pressure fan 2, the power input end of the sun gear 13 is fixedly welded to the gas turbine shaft 12, or the power input end of the sun gear 13 is integrally formed with the gas turbine shaft 12, a plurality of planet gears 14 are arranged for planetary rotation about one or more sun gears 13 within one or more ring gears 16, the plurality of planet gears 14 collectively driving a planet carrier 15, the plurality of planet gears 14 all being of equal diameter and equal axial length.
The position that is close to adjustable angle middling pressure fan 2 between outer culvert 6 and well culvert 7 is provided with preceding variable area culvert ejector 9 for adjust the inlet flow ratio of outer culvert 6 and well culvert 7, be close to between well culvert 7 and the interior culvert 8 rear end and be provided with back variable area culvert ejector 10 for adjust the export airflow ratio of well culvert 7 and interior culvert 8, the apex of fan 1 is close to the outside of outer culvert 6 before the adjustable angle, and the apex of adjustable angle middling pressure fan 2 is close to the outside of well culvert 7.
The gas turbine 5 drives the high-pressure compressor 3 and the differential planetary reducer 11 through a gas turbine shaft 12, and drives the angle-adjustable front fan 1 and the angle-adjustable medium-pressure fan 2 through the output of the differential planetary reducer 11; three airflow channels of an outer culvert 6, a middle culvert 7 and an inner culvert 8 are formed through different airflow directions.
By adjusting the opening and closing of the duct adjusting mechanism, namely the front variable-area duct ejector 9 and the rear variable-area duct ejector 10 and synchronously adjusting the angles of the angle-adjustable front fan 1 and the angle-adjustable medium-pressure fan 2, the duct ratio can be adjusted in a large range, and the specific variable circulation mode comprises the following steps:
the first mode is as follows: the front variable-area bypass ejector 9 is located at a position a, the rear variable-area bypass ejector 10 is located at a position e, the engine is in a three-bypass mode with a culvert 6, a culvert 7 and an internal culvert 8, and most of airflow is discharged through the culvert 6 and the culvert 7;
and a second mode: the front variable-area bypass ejector 9 is located at the position b, the rear variable-area bypass ejector 10 is located at the position e, most of work is absorbed by the angle-adjustable front fan 1 by adjusting the angles of the angle-adjustable front fan 1 and the angle-adjustable medium-pressure fan 2, the angle-adjustable medium-pressure fan 2 can realize the function of a compressor pressure increasing level with a lower pressure ratio (in the limit condition, the medium-pressure fan can be approximately stopped to rotate), and the engine is in a bypass mode of a bypass 7 flowing mode and a bypass 8 flowing mode;
and a third mode: the front variable-area bypass ejector 9 is located at a position c, the rear variable-area bypass ejector 10 is located at a position d, the static pressure of the front fan is equivalent to that of the outlet of the medium-pressure fan by reasonably adjusting the angles of the angle-adjustable front fan 1 and the angle-adjustable medium-pressure fan 2, so that the loss is small when the external culvert 6 is mixed, and the engine is in a bypass mode of flowing of the external culvert 6 and flowing of the internal culvert 8;
and a fourth mode: preceding variable area duct ejector 9 is located position b, variable area duct ejector 10 is located position d after, through fan 1 before adjusting adjustable angle, the angle of adjustable angle middling pressure fan 2 for most merit is absorbed by the middling pressure fan, and fan 1 can realize the function of the lower high through-flow fan of pressure ratio (under the limit condition, can approximate stall) before the adjustable angle this moment, and this time the culvert 6, the culvert 7 is closed, and the engine performance is the single duct turbojet mode of flowing of culvert 8.
The invention adopts a single-rotor gas turbine 5 to drive a high-pressure compressor 3 and a differential planetary reducer 11, the differential planetary reducer 11 drives a variable-angle fan and a supercharger, and a duct injection valve is used for controlling the trend of an airflow path, so that a novel variable-cycle gas turbine engine adopting a single-rotor mode is formed.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. The utility model provides a novel become circulation gas turbine engine, its characterized in that, is including adjustable angle preceding fan (1), adjustable angle middling pressure fan (2), differential planetary reducer (11) and gas turbine shaft (12), differential planetary reducer (11) include sun gear (13), planetary gear (14), planet carrier (15) and ring gear (16), sun gear (13) and the coaxial fixed connection of gas turbine shaft (12), planet carrier (15) are connected with adjustable angle preceding fan (1) drive, ring gear (16) are connected with adjustable angle middling pressure fan (2) drive.
2. The novel variable-cycle gas turbine engine as claimed in claim 1, further comprising three airflow channels including an outer culvert (6), a middle culvert (7) and an inner culvert (8), wherein a front variable-area culvert ejector (9) is arranged between the outer culvert (6) and the middle culvert (7) and close to the angle-adjustable medium-pressure fan (2) and used for adjusting the air intake flow ratio of the outer culvert (6) and the middle culvert (7), and a rear variable-area culvert ejector (10) is arranged between the middle culvert (7) and the inner culvert (8) and close to the rear end of the inner culvert (8) and used for adjusting the outlet air flow ratio of the middle culvert (7) and the inner culvert (8).
3. A new variable cycle gas turbine engine according to claim 2, characterized in that the tip of the adjustable angle front fan (1) is close to the outside of the culvert (6).
4. The new variable cycle gas turbine engine according to claim 2, characterized in that the tips of the adjustable angle medium pressure fans (2) are close to the outside of the culvert (7).
5. A new variable cycle gas turbine engine according to claim 4, characterized in that the differential planetary reducer (11) is placed between the angle adjustable front fan (1) and the angle adjustable medium pressure fan (2).
6. The novel variable cycle gas turbine engine as claimed in claim 1, wherein the power input end of the sun gear (13) is fixedly welded to the gas turbine shaft (12), or the power input end of the sun gear (13) is integrally formed with the gas turbine shaft (12).
7. A novel variable cycle gas turbine engine according to claim 1, characterized in that a plurality of said planet gears (14) are arranged in one or more ring gears (16) for planetary rotation around one or more sun gears (13), the plurality of planet gears (14) driving together a planet carrier (15).
8. A novel variable cycle gas turbine engine as claimed in claim 7 wherein a plurality of said planet gears (14) are all of equal diameter and equal axial length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111187082.1A CN113864083A (en) | 2021-10-12 | 2021-10-12 | Novel variable-cycle gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111187082.1A CN113864083A (en) | 2021-10-12 | 2021-10-12 | Novel variable-cycle gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113864083A true CN113864083A (en) | 2021-12-31 |
Family
ID=78998757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111187082.1A Pending CN113864083A (en) | 2021-10-12 | 2021-10-12 | Novel variable-cycle gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113864083A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856856A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
| CN115506916A (en) * | 2022-08-30 | 2022-12-23 | 中国航发湖南动力机械研究所 | Contra-rotating blade tip dual-drive turbofan engine |
| CN115680940A (en) * | 2022-10-15 | 2023-02-03 | 中国科学院力学研究所 | Crown turbine variable-cycle turbine rocket engine and engine thrust implementation method |
| CN116085142A (en) * | 2023-04-11 | 2023-05-09 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090074565A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Turbine engine with differential gear driven fan and compressor |
| CN103867337A (en) * | 2012-12-11 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Variable cycle engine with high bypass ratio |
| US20180209350A1 (en) * | 2017-01-23 | 2018-07-26 | United Technologies Corporation | Advanced Geared Gas Turbine Engine |
| CN110259600A (en) * | 2019-06-25 | 2019-09-20 | 中国航空发动机研究院 | Double outer adaptive cycle engines of culvert |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
-
2021
- 2021-10-12 CN CN202111187082.1A patent/CN113864083A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090074565A1 (en) * | 2004-12-01 | 2009-03-19 | Suciu Gabriel L | Turbine engine with differential gear driven fan and compressor |
| CN103867337A (en) * | 2012-12-11 | 2014-06-18 | 中航商用航空发动机有限责任公司 | Variable cycle engine with high bypass ratio |
| US20180209350A1 (en) * | 2017-01-23 | 2018-07-26 | United Technologies Corporation | Advanced Geared Gas Turbine Engine |
| CN110259600A (en) * | 2019-06-25 | 2019-09-20 | 中国航空发动机研究院 | Double outer adaptive cycle engines of culvert |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
Non-Patent Citations (1)
| Title |
|---|
| 陈仲光等: "基于常规涡扇发动机发展变循环发动机的研究", 《沈阳航空航天大学学报》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114856856A (en) * | 2022-05-06 | 2022-08-05 | 中国科学院工程热物理研究所 | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine |
| CN114856856B (en) * | 2022-05-06 | 2024-04-30 | 中国科学院工程热物理研究所 | High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine |
| CN114934857A (en) * | 2022-07-21 | 2022-08-23 | 中国航发四川燃气涡轮研究院 | Variable-cycle turbine engine |
| CN115506916A (en) * | 2022-08-30 | 2022-12-23 | 中国航发湖南动力机械研究所 | Contra-rotating blade tip dual-drive turbofan engine |
| CN115680940A (en) * | 2022-10-15 | 2023-02-03 | 中国科学院力学研究所 | Crown turbine variable-cycle turbine rocket engine and engine thrust implementation method |
| CN116085142A (en) * | 2023-04-11 | 2023-05-09 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
| CN116085142B (en) * | 2023-04-11 | 2023-05-30 | 北京航空航天大学 | Novel overall structure of interstage combustion variable cycle engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113864083A (en) | Novel variable-cycle gas turbine engine | |
| US7107756B2 (en) | Turbofan arrangement | |
| US7730714B2 (en) | Turbofan gas turbine engine with variable fan outlet guide vanes | |
| RU2631956C2 (en) | Gear fan-type gas-turbine motor arrangement | |
| CN109339875B (en) | A kind of mixing diffuser of band bypass bleed | |
| CA2690665A1 (en) | Gas turbine engine assembly and methods of assembling same | |
| CN203906118U (en) | Gas cooling system for turbine-based combined-cycle engine | |
| CN102305152A (en) | Hybrid exhaust aircraft engine | |
| CN104454034B (en) | Push-in double containment variable-nozzle turbocharger | |
| CN108518289A (en) | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan | |
| CN208831104U (en) | A kind of gear drive fanjet | |
| CN203906120U (en) | Combined engine for unmanned combat aircraft | |
| WO2012019419A1 (en) | Wind-driven turbine ramjet engine | |
| CN113738531A (en) | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine | |
| CN109595041B (en) | Variable-circulation large-bypass-ratio turbofan engine | |
| CN203906119U (en) | Turbine-based combined cycle engine of wide flight envelope aircraft | |
| CN107100719B (en) | A kind of turbocharger in axially variable section | |
| CN201474730U (en) | Pneumatic nozzle of turbocharger with variable geometry | |
| CN115962065A (en) | Rotary stamping shock wave supercharging gas turbine engine | |
| CN111120102A (en) | Turbofan engine pneumatic layout structure with high-pressure shaft directly driving booster stage | |
| CN203847273U (en) | Fan system for turbine-based combined cycle engine | |
| CN112780400B (en) | Special booster for high-altitude power recovery of aviation piston engine | |
| CN208587220U (en) | A kind of axial displacement turbocharger | |
| CN208578933U (en) | For the linkage between booster and air compressor machine | |
| CN115506916B (en) | Double-drive turbofan engine with contra-rotating blade tips |
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 | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211231 |
|
| RJ01 | Rejection of invention patent application after publication |