阅读说明：本技术 一种新型变循环燃气涡轮发动机 (Novel variable-cycle gas turbine engine ) 是由 黄兴 丁金涛 罗潇 张丽娜 曹俊 李维 于 2021-10-12 设计创作，主要内容包括：本发明公开了一种新型变循环燃气涡轮发动机,属于燃气涡轮发动机技术领域。包括可调角度前风扇、可调角度中压风扇和差动行星减速器,太阳齿轮与燃气涡轮轴同轴固定连接,行星架与可调角度前风扇驱动连接,环形齿轮与可调角度中压风扇驱动连接,采用单转子燃气涡轮驱动高压压气机及差动行星齿轮减速器,差动行星减速器驱动可变角度的风扇及增压机,辅以涵道引射阀控制气流流路走向,形成一种采用单转子模式的变循环燃气涡轮发动机,代替传统的多转子变循环燃气涡轮发动机,简化涡扇发动机支承并减低转子结构系统复杂度,降低发动机结构的设计难度,使得燃气涡轮发动机具备更多的循环模式,更适应于复杂的飞行状态。(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.)

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.

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.