CN114576006B

CN114576006B - Engine and aircraft

Info

Publication number: CN114576006B
Application number: CN202210233954.1A
Authority: CN
Inventors: 苗辉; 周琨; 马薏文; 李亚忠
Original assignee: China Aero Engine Research Institute
Current assignee: China Aero Engine Research Institute
Priority date: 2022-03-10
Filing date: 2022-03-10
Publication date: 2023-09-22
Anticipated expiration: 2042-03-10
Also published as: CN114576006A

Abstract

The application discloses an engine and an aircraft, which comprise an air inlet nose cone, an engine outer shell, an engine inner shell, an inner turbine engine and an outer turbine engine, wherein the air inlet nose cone is arranged on the engine outer shell; the engine outer shell is coaxially arranged with the engine inner shell, and a gas channel is formed between the engine inner shell and the engine outer shell; a channel casing is arranged in the gas channel, and the gas channel is divided into an inner gas channel and an outer gas channel from inside to outside through the channel casing; a series mode switching valve is arranged between the inner gas channel and the outer gas channel; the inner turbine engine is arranged in the inner gas channel, and the outer turbine engine is arranged in the outer gas channel between the inner compressor and the inner main combustion chamber of the inner turbine engine; under the action of the serial mode switching valve, the working switching of the turbine engine in a low-speed state, a medium-speed state or a high-speed state is realized; thereby meeting the different requirements of the aviation turbine engine on the cyclic pressure ratio and the air inlet temperature in low-speed and high-speed flight.

Description

Engine and aircraft

Technical Field

The application belongs to the technical field of aeroengines, and particularly relates to an engine and an aircraft.

Background

With the technical development of the traditional aero-engine, a variable cycle engine concept appears, and the variable cycle engine becomes the main stream direction. Variable cycle engines achieve different characteristic thermodynamic cycles by adjusting the geometry, dimensions, or positions of some components of the engine, changing engine cycle parameters. The adjusting capability of the engine is enhanced, the engine is promoted to change the working state in a wider range, and the adaptability of the engine to complex and changeable tasks is greatly enhanced.

The main technical scheme of the variable cycle engine is as follows: variable fans, turbine blade tip fans, front air turbines, and the like. The first variable cycle engine validator XA100 engine from GE in the united states has been tested 3 months in 2021. The intended goals of a 10% increase in thrust and a 25% increase in fuel efficiency are achieved. The technology pressing is realized on aeroengine technologies of other countries.

The flying speed range of the aero-engine is generally Ma 0-2, and the main purpose of the technical approach of the variable cycle engine is to further increase the working capacity in a low-speed state, increase the thrust and reduce the oil consumption. The measure is mainly to increase the circulation capacity of the external air flow.

However, the idea of variable cycle of the aero-engine can be used for increasing the speed and extending the flying speed range to Ma3 to 4. The air compressor is required to provide higher pressure ratio (such as 25-30) when the aeroengine flies at low speed so as to ensure higher cycle efficiency and lower oil consumption. And the supercharging effect of the air inlet channel is gradually obvious in the high-speed flight above Ma3, so that the compressor is required to provide a lower supercharging ratio (less than 10). The variable circulation mode is adopted to realize the large-scale adjustment of the supercharging ratio of the compressor, so that the variable circulation type compressor is an effective wide-speed-range engine scheme, and the variable circulation mode is a little more popular.

Disclosure of Invention

In order to solve the defects in the prior art, the application provides an engine and an aircraft, and the design is used for designing a wide-speed-range engine by adopting a serial-parallel connection mode of two engines aiming at different requirements of aviation turbine engines on the cycle pressure ratio and the air inlet temperature in low-speed and high-speed flight.

The technical scheme adopted by the application is as follows:

an engine, comprising:

an engine outer case;

an engine inner case coaxially disposed with the engine outer case; the engine outer shell is sleeved outside the engine inner shell;

the channel casing is arranged between the engine outer shell and the engine inner shell; an inner gas channel is formed between the channel casing and the engine inner shell, and an outer gas channel is formed between the channel casing and the outer shell; the channel casing is provided with an opening;

the serial mode switching valve is arranged at the opening of the channel casing, and the flow direction of gas between the inner gas channel and the outer gas channel can be changed by switching the serial mode switching valve;

an inner turbine engine disposed in the inner gas passage;

an outer turbine engine disposed in the outer gas passage;

an inner gas passage switch structure provided at an intake end of the inner gas passage; the method comprises the steps of,

and the precooling channel switching valve is arranged at the air inlet end of the outer air channel.

Further, the channel casing has a first opening and a second opening; the first opening and the second opening divide the channel casing into a first channel casing, a second channel casing and a third channel casing in sequence along the gas flowing direction;

the series mode switching valve comprises a first switching valve arranged at the first opening and a second switching valve arranged at the second opening.

Further, the inner turbine engine comprises an inner compressor, an inner main combustion chamber and an inner turbine which are sequentially arranged along the gas flowing direction, wherein the inner compressor is arranged between the first channel casing and the inner engine casing, and the inner main combustion chamber and the inner turbine are arranged between the third channel casing and the inner engine casing;

the outer turbine engine comprises an outer compressor, an outer main combustion chamber and an outer turbine which are sequentially arranged along the gas flowing direction, wherein the outer compressor, the outer main combustion chamber and the outer turbine are arranged between the second channel casing and the engine outer shell.

Further, the inner turbine engine further includes an inner turbine shaft disposed along a central engine axis;

the outer turbine engine also includes an outer turbine shaft disposed within the outer gas passage.

Further, the engine further includes: the precooling heat exchanger is arranged between the first channel casing and the engine outer shell.

Further, the engine further includes: afterburner disposed at the ends of the inner and outer gas passages, and afterburner injection bars disposed within the afterburner.

Further, the inner gas passage switch structure is designed as a tapered structure.

Further, the inner gas passage switch structure is connected with the actuating mechanism, and the actuating mechanism drives the inner gas passage switch structure to axially move.

Further, when ma=0 to 1.5, the inner gas passage air inlet end is opened, the outer gas passage air inlet end is closed, the first opening is opened, the second opening is opened, the outer gas passage air outlet end is closed, the inner gas passage and the outer gas passage are communicated in series, and the inner turbine engine and the outer turbine engine are connected in series.

Further, when ma=1.5 to 2.8, the inner gas channel and the outer gas channel are both opened, the first opening is closed, the second opening is closed, the inner gas channel and the outer gas channel are both passages, and the inner turbine engine and the outer turbine engine are connected in parallel.

Further, when Ma >2.8, the inner gas passage is closed, the outer gas passage inlet end is opened, the first opening is closed, and the second opening is closed; the outer gas channel is a passage; the inner turbine engine is not in operation and the outer turbine engine is in operation.

An aircraft is provided with the engine.

The application has the beneficial effects that:

(1) The engine designed by the application has the advantages that through the serial-parallel connection switching between the inner turbine engine and the outer turbine engine, the total pressure ratio is equal to the product of the pressure ratios of the two engines at low speed, and only the outer turbine engine with smaller pressure ratio works at high speed, so that the large-scale adjustment of the cyclic pressure ratio can be conveniently realized, the different requirements of the engines on the total pressure ratio at high speed and low speed are solved, and the ultra-high speed flight condition of more than Ma3 is satisfied.

(2) On the premise of adjusting the cyclic pressure ratio in a large range, the flying speed limit of the engine can be greatly expanded, and the performance of the engine in a high-low speed state can be considered.

Drawings

FIG. 1 is a cross-sectional view of a high speed aircraft turbine engine of the present application;

FIG. 2 is a schematic illustration of the fluid flow of the high speed aircraft turbine engine of the present application in a low speed mode;

FIG. 3 is a schematic illustration of the fluid flow of the high speed aircraft turbine engine of the present application in medium speed mode;

FIG. 4 is a schematic illustration of the fluid flow of the high speed aircraft turbine engine of the present application in a high speed mode;

in the figure, 1, an air inlet nose cone, 2, a precooling heat exchanger, 3, an outer compressor, 4, an outer main combustion chamber, 5, an outer turbine, 6, a serial mode switching valve, 7, an inner turbine shaft, 8, an afterburner oil injection rod, 9, an inner turbine, 10, an inner main combustion chamber, 11, an inner compressor, 12, a precooling channel switching valve, 13, an outer turbine shaft, 14, an engine shell, 15, a part name, 16, a channel casing, 16a, a first channel casing, 16b, a second channel casing, 16c, a third channel casing, 17, an inner compressor guide vane, 18, an outer compressor guide vane, 19, a first opening, 20 and a second opening.

Detailed Description

The present application will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present application more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the application.

As shown in fig. 1, the present engine is composed of an engine outer case 14 and an engine inner case 15. The engine outer case 14 is coaxially provided outside the engine inner case 15, so that an annular gas passage is formed between the engine inner case 15 and the engine outer case 14. A passage case 16 is provided in a gas passage between the engine inner case 15 and the engine outer case 14, an inner gas passage is formed between the passage case 16 and the engine inner case 15, and an outer gas passage is formed between the passage case 16 and the outer case 14.

Referring to the drawings, the channel casing 16 has openings, a first opening 19 and a second opening 20, respectively; the first opening 19 and the second opening 20 divide the channel casing 16 into a first channel casing 16a, a second channel casing 16b and a third channel casing 16c in this order along the gas flow direction.

And a series mode switching valve 6 is arranged in a gap between the first channel casing and the second channel and a gap between the second channel casing and the third channel casing. In this embodiment, the serial mode switching valve 6 is composed of two parts, the first part is installed at the first opening 19, the other part is installed at the second opening 20, and by changing the angles of the two parts of the serial mode switching valve 6, the opening or closing of the first opening 19 and the second opening 20 is realized, so that the flowing direction of the gas in the inner gas channel and the outer gas channel is changed.

An inner gas channel switch structure 1 is arranged at the front end of the engine, and the tail part of the inner gas channel switch structure 1 is arranged towards the air inlet end of the inner gas channel; the inner gas passage inlet end may be opened or closed.

More preferably, the inner gas passage switch structure 1 is designed as an air inlet nose cone 1, the cone tip part of the air inlet nose cone 1 faces to the air inlet end, and the tail part of the air inlet nose cone 1 faces to the air inlet end of the inner gas passage.

The engine consists of two turbine engines which are coaxially arranged and respectively called an inner turbine engine and an outer turbine engine.

More specifically, the internal turbine engine includes an internal compressor 11, an internal main combustion chamber 10, and an internal turbine 9 that are disposed in this order in the gas flow direction, wherein the internal compressor 11 is disposed between a first passage casing 16a and an engine inner casing 15, and the internal main combustion chamber 10 and the internal turbine 9 are disposed between a third passage casing 16c and the engine inner casing 15. The inner turbine shaft 7 is arranged along the central axis of the engine, and inner compressor guide blades 17 are arranged at the inner compressor 11 and between the inner main combustion chamber 10 and the inner turbine 9.

The outer turbine engine comprises an outer compressor 3, an outer main combustion chamber 4 and an outer turbine 5 which are sequentially arranged along the gas flow direction, wherein the outer compressor 3, the outer main combustion chamber 4 and the outer turbine 5 are arranged between a second channel casing 16b and an engine outer shell 14. The outer turbine engine is disposed in a position between the inner compressor 11 and the inner main combustion chamber 10 of the inner turbine engine, as seen in the axial direction. The outer turbine shaft 13 of the outer turbine engine is sleeved outside the second channel casing through a bearing as seen in the radial direction; i.e., the outer turbine engine is disposed within the outer gas passage. Along the gas flow direction, an outer compressor 3, an outer main combustion chamber 4 and an outer turbine 5 are arranged in sequence.

More preferably, the tail end in the gas channel is an afterburner, an afterburner oil injection rod 8 is arranged in the afterburner, and the inner turbine engine and the outer turbine engine share one afterburner and are used for oil supply and combustion through the afterburner oil injection rod.

More preferably, the pre-cooling heat exchanger 2 is further arranged at the air inlet end, and the pre-cooling heat exchanger 2 is circumferentially arranged in an outer gas channel at the first channel casing 16a, wherein the channel is a pre-cooling channel. And a pre-cooling channel switch valve 12 is arranged at two ends of the pre-cooling channel. The pre-cooling channel switching valve 12 is composed of two parts, a switching valve at the air inlet end of the pre-cooling channel is arranged on the inner wall of the engine outer shell 14, a switching valve at the air outlet end of the pre-cooling channel is arranged on the right side of the first channel casing 16a, and the pre-cooling channel is opened or closed through rotation of the pre-cooling channel switching valves 12 at the two ends of the pre-cooling channel.

More preferably, the air inlet nose cone 1 is movable along the axial direction, and when the air inlet nose cone moves backwards, the tail part of the air inlet nose cone 1 can be matched with the air inlet end of the inner gas channel, as shown in fig. 4 (high-speed mode), so that the inner gas channel where the inner turbine engine is located can be completely covered. In the application, the air inlet nose cone 1 is provided with an actuating mechanism, the air inlet nose cone 1 is driven by the actuating mechanism to move along the axial direction, and the air inlet nose cone 1 and the actuating mechanism thereof are also independently hoisted on an airplane, and the engine is not hard-connected. The actuating mechanism can be formed by combining a driving motor, an output shaft, a connecting rod mechanism and the like, and the air inlet nose cone 1 is driven to move by the driving motor and the connecting rod mechanism connected with the output shaft.

In the design of system circulation, the supercharging ratio of the internal turbine engine is higher and reaches about 8; the supercharging of the outer turbine engine is relatively low and reaches about 3. The outer turbine engine is the only power when flying at the highest speed, so the compression ratio is low. In this case, the boost ratio is considered to be determined by the number of series stages of the compressor rotor.

Meanwhile, in the application, an aircraft is also provided, and the aircraft is loaded with the high-speed aviation turbine engine based on series-parallel connection.

For a clearer description of the structure of a turbine engine according to the present application, the following is a further explanation of the operation of an aircraft in which the turbine engine is installed.

The flow path switching of three states of the engine can be realized by means of the air inlet nose cone 1, the precooling channel switching valve 12 and the serial mode switching valve 6:

(1) In a low-speed state, for example, ma=0-1.5, the air inlet end of the inner gas channel is opened when the air inlet nose cone 1 moves forwards, the pre-cooling channel switching valve 12 is closed, the air inlet end of the outer gas channel is closed, the first opening 19 is opened, the second opening 20 is opened, the air outlet end of the outer gas channel is closed, the inner gas channel and the outer gas channel are communicated in series, and the inner turbine engine and the outer turbine engine are connected in series as shown in fig. 2; the air flow enters from the inner air passage and sequentially passes through the inner air compressor 11, the outer air compressor 3, the outer main combustion chamber 4, the outer turbine 5, the inner main combustion chamber 10, the inner turbine 9 and the afterburner; the inner main combustor 10 at this point corresponds to the function of an "inter-stage combustor" of a conventional turbine engine.

In this mode, the actual boost ratio of the inner turbine engine is about 8, the actual boost ratio of the outer turbine engine is 3-4, the total boost ratio in low-speed flight is about 25, and the actual boost ratio is the main flow level of the current low-bypass-ratio military turbine engine, so that the engine has better low-speed performance.

(2) In a medium speed state, for example, ma=1.5-2.8, the inlet nose cone 1 moves forward, namely, the inner gas channel is opened, the precooling channel switching valve 12 is opened, namely, the outer gas channel is opened, the first opening 19 is closed, the second opening 20 is closed, the inner gas channel and the outer gas channel are both channels, and the inner turbine engine and the outer turbine engine are connected in parallel. At this point, the pre-cooling passage is opened and the air flow entering the engine is split into two paths as shown in fig. 3, entering from the inner turbine engine and the outer turbine engine, respectively.

The two streams each travel their own air flow path and mix before the afterburner.

(3) In a high-speed state, for example, ma >2.8, the air inlet nose cone 1 moves backwards, namely the inner air channel is closed, the precooling channel switching valve 12 is opened, namely the air inlet end of the outer air channel is opened, the first opening 19 is closed, and the second opening 20 is closed; at this time, the inner gas channel is closed, the outer gas channel is a passage, namely the inner turbine engine does not work, and only the outer turbine engine works; the air flow sequentially passes through the precooling heat exchanger 2, the outer air compressor 3, the outer main combustion chamber 4, the outer turbine 5 and the afterburner.

The supercharging ratio of the compression system is only about 3 at high speed, and the engine can work in a state with extremely high speed even reaching Ma 4-5 by matching with the pre-cooling heat exchanger 2.

The above embodiments are merely for illustrating the design concept and features of the present application, and are intended to enable those skilled in the art to understand the content of the present application and implement the same, the scope of the present application is not limited to the above embodiments. Therefore, all equivalent changes or modifications according to the principles and design ideas of the present application are within the scope of the present application.

Claims

1. An engine, comprising:

an engine outer case (14);

an engine inner case (15) coaxially provided with the engine outer case (14); the engine outer shell (14) is sleeved outside the engine inner shell (15);

a channel casing (16) provided between the engine outer case (14) and the engine inner case (15); an inner gas channel is formed between the channel casing (16) and the engine inner shell (15), and an outer gas channel is formed between the channel casing (16) and the outer shell (14); the channel casing (16) has an opening;

a serial mode switching valve (6) provided at an opening of the channel case (16), the serial mode switching valve (6) being capable of changing a flow direction of gas between an inner gas channel and an outer gas channel by switching on and off;

an inner turbine engine disposed in the inner gas passage;

an outer turbine engine disposed in the outer gas passage;

an inner gas passage switching structure (1) provided at an intake end of the inner gas passage; the method comprises the steps of,

a pre-cooling channel switching valve (12) provided at an air inlet end of the outer gas channel;

the channel casing (16) has a first opening (19) and a second opening (20); the first opening (19) and the second opening (20) divide the channel casing (16) into a first channel casing (16 a), a second channel casing (16 b) and a third channel casing (16 c) in sequence along the gas flow direction;

the series mode switching valve (6) comprises a first switching valve arranged at a first opening (19) and a second switching valve arranged at a second opening (20);

when ma=0-1.5, the inner gas channel air inlet end is opened, the outer gas channel air inlet end is closed, the first opening (19) is opened, the second opening (20) is opened, the outer gas channel air outlet end is closed, the inner gas channel and the outer gas channel are communicated in series, and the inner turbine engine and the outer turbine engine are connected in series;

when ma=1.5-2.8, the inner gas channel and the outer gas channel are both opened, the first opening (19) is closed, the second opening (20) is closed, the inner gas channel and the outer gas channel are both passages, and the inner turbine engine and the outer turbine engine are connected in parallel;

when Ma is more than 2.8, the inner gas channel is closed, the gas inlet end of the outer gas channel is opened, the first opening (19) is closed, and the second opening (20) is closed; the outer gas channel is a passage; the inner turbine engine is not in operation and the outer turbine engine is in operation.

2. The engine according to claim 1, characterized in that the internal turbine engine comprises an internal compressor (11), an internal main combustion chamber (10) and an internal turbine (9) arranged in sequence in the direction of gas flow, wherein the internal compressor (11) is arranged between a first channel casing (16 a) and an engine inner housing (15), and the internal main combustion chamber (10) and the internal turbine (9) are arranged between a third channel casing (16 c) and the engine inner housing (15);

the outer turbine engine comprises an outer compressor (3), an outer main combustion chamber (4) and an outer turbine (5) which are sequentially arranged along the gas flowing direction, wherein the outer compressor (3), the outer main combustion chamber (4) and the outer turbine (5) are arranged between a second channel casing (16 b) and an engine outer shell (14).

3. The engine according to claim 2, characterized in that the inner turbine engine further comprises an inner turbine shaft (7) arranged along the central axis of the engine;

the outer turbine engine further includes an outer turbine shaft (13) disposed within the outer gas passage.

4. The engine of claim 1, wherein the engine further comprises: and a pre-cooling heat exchanger (2) arranged between the first channel casing (16 a) and the engine outer shell (14).

5. The engine of any one of claims 1-4, further comprising: afterburner disposed at the ends of the inner and outer gas passages, and an afterburner injection rod (8) is disposed within the afterburner.

6. An engine according to claim 5, characterized in that the inner gas passage switch structure (1) is designed as a conical structure.

7. The engine according to claim 5, characterized in that the inner gas passage switch structure (1) is connected to an actuating mechanism, and the actuating mechanism drives the inner gas passage switch structure (1) to move in the axial direction.

8. An aircraft equipped with an engine according to any one of claims 1 to 7.