Turbine interstage combustion chamber supersonic cruise engine and control method thereof

Abstract

The invention belongs to the technical field of turbine engine design, and particularly relates to a turbine interstage combustion chamber supersonic cruise engine and a control method thereof.The turbine interstage combustion chamber supersonic cruise engine comprises a fan adopting a FLADE fan; the gas compressor is arranged behind the fan; the main combustion chamber is arranged behind the gas compressor; the high-pressure turbine is arranged behind the main combustion chamber and is connected with the gas compressor through a high-pressure shaft; the mixing chamber is arranged behind the high-pressure turbine and is communicated with the fan through an outer duct; the interstage combustion chamber is arranged behind the mixing chamber; the low-pressure turbine is arranged behind the combustion chamber and is connected with the fan through a low-pressure shaft; the spraying pipe is arranged on the low-pressure turbine; and after the injection valve is arranged on the high-pressure turbine, the injection valve deflects to the inner runner surface of the outer duct when the injection valve is opened, and deflects to the outer runner surface of the outer duct when the injection valve is closed.

Description

Technical Field

[0001] This application belongs to the technical field of turbine engine design, and particularly relates to a turbine inter-stage combustion chamber supersonic cruise engine and its control method. Background Technique

[0002] When a turbine engine performs supersonic cruise, a large thrust is required. For this purpose, it is mostly achieved by increasing the engine temperature level, using an afterburner or an inter-stage combustion chamber.

[0003] By increasing the engine temperature level to increase the thrust of the turbine engine, higher requirements are imposed on the combustion organization of the main combustion chamber and the materials and cooling technologies of the hot-end components, increasing the design difficulty and service life of the engine, and making certain sacrifices in terms of engine size, weight, pollutant emissions, etc.

[0004] Adopting the afterburner scheme to increase the thrust of the turbine engine has a high fuel consumption rate and is difficult to support long-term operation.

[0005] Adopting the inter-stage combustion chamber scheme to increase the thrust of the turbine engine includes an inter-stage combustion chamber scheme without external bypass air oxygen supplementation and an inter-stage combustion chamber scheme with external bypass air oxygen supplementation. Under the same thermal efficiency, it can reduce the temperature before the high-pressure turbine and maintain a low fuel consumption rate. However, for the inter-stage combustion chamber scheme without external bypass air oxygen supplementation, the oxygen content in the inlet air of the inter-stage combustion chamber is relatively low, making it difficult to reach a high combustion temperature and combustion efficiency; for the inter-stage combustion chamber scheme with external bypass air oxygen supplementation, usually at high Mach numbers, the pressure of the external bypass air is much lower than the pressure after the high-pressure turbine, and it is difficult for the external bypass air to enter the inter-stage combustion chamber, resulting in an external bypass air mixing problem.

[0006] In view of the existence of the above technical defects, this application is proposed. Summary of the Invention

[0007] The purpose of this application is to provide a turbine inter-stage combustion chamber supersonic cruise engine and its control method to overcome or mitigate at least one aspect of the known technical defects.

[0008] The technical solution of this application is as follows:

[0009] On the one hand, a turbine inter-stage combustion chamber supersonic cruise engine is provided, including:

[0010] A fan, using a FLADE fan;

[0011] A compressor, arranged behind the fan;

[0012] A main combustion chamber, arranged behind the compressor;

[0013] A high-pressure turbine, arranged behind the main combustion chamber and connected to the compressor through a high-pressure shaft;

[0014] The mixing chamber is arranged behind the high-pressure turbine and is connected to the fan through the bypass duct;

[0015] The inter-stage combustion chamber is arranged behind the mixing chamber;

[0016] The low-pressure turbine is arranged behind the combustion chamber and is connected to the fan through the low-pressure shaft;

[0017] The nozzle is arranged on the low-pressure turbine;

[0018] The ejector valve is arranged behind the high-pressure turbine. When it is opened wide, it deflects towards the inner flow path surface of the bypass duct, and when it is closed, it deflects towards the outer flow path surface of the bypass duct.

[0019] According to at least one embodiment of the present application, in the above turbine inter-stage combustion chamber supersonic cruise engine, the inter-stage combustion chamber adopts a hydrogen combustion chamber.

[0020] According to at least one embodiment of the present application, in the above turbine inter-stage combustion chamber supersonic cruise engine, the inter-stage combustion chamber adopts a micro-mixing non-premixed diffusion combustion technology.

[0021] On the other hand, a method for controlling a turbine inter-stage combustion chamber supersonic cruise engine is provided to control the above turbine inter-stage combustion chamber supersonic cruise engine, which is characterized by including:

[0022] When the Mach number increases, open the ejector valve and adjust to balance the bypass air pressure and the high-pressure turbine outlet pressure;

[0023] When the Mach number decreases, close the ejector valve and adjust to balance the bypass air pressure and the high-pressure turbine outlet pressure. Description of the Drawings

[0024] Figure 1 is a schematic diagram of a turbine inter-stage combustion chamber supersonic cruise engine provided by an embodiment of the present application;

[0025] Wherein:

[0026] 1 - fan; 2 - compressor; 3 - main combustion chamber; 4 - high-pressure turbine; 5 - mixing chamber; 6 - inter-stage combustion chamber; 7 - nozzle; 8 - nozzle; 9 - ejector valve.

[0027] For better illustration of this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product. In addition, the drawings are only for illustrative purposes and cannot be construed as a limitation of the present application. Detailed Embodiments

[0028] To make the technical solution of this application and its advantages clearer, the following will further describe the technical solution of this application clearly and completely in conjunction with the accompanying drawings. It can be understood that the specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application and not to limit this application. It should be noted that for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design.

[0029] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should be the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The terms indicating directions used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the object being described changes, its relative positional relationship may also change accordingly. The "including" used in the description of this application means that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0030] In addition, it should be noted that unless otherwise clearly specified and limited, the terms such as "installation" and "connection" used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. Those skilled in the art can understand their specific meanings in this application according to the specific situation.

[0031] On the one hand, a supersonic cruise engine with an inter-stage combustion chamber for a turbine is provided, including:

[0032] A fan 1, adopting a FLADE fan;

[0033] A compressor 2, arranged behind the fan 1;

[0034] A main combustion chamber 3, arranged behind the compressor 2;

[0035] A high-pressure turbine 4, arranged behind the main combustion chamber 3, and connected to the compressor 2 through a high-pressure shaft;

[0036] A mixing chamber 5, arranged behind the high-pressure turbine 4, and connected to the fan 1 through an outer bypass duct, that is, connected to the outer bypass of the FLADE fan;

[0037] An inter-stage combustion chamber 6, arranged behind the mixing chamber 5;

[0038] A low-pressure turbine 7, arranged behind the combustion chamber 6, and connected to the fan 1 through a low-pressure shaft;

[0039] A nozzle 8, arranged on the low-pressure turbine 7;

[0040] The ejector valve 9 is arranged behind the high-pressure turbine 4 and can partially extend into the mixing chamber 5. When it is fully open, it deflects towards the inner flow path surface of the outer bypass duct, and when it is closed, it deflects towards the outer flow path surface of the outer bypass duct.

[0041] When the supersonic cruise engine with an inter-stage combustion chamber disclosed in the above embodiment operates, air enters the engine. After being compressed by the fan 1, it will be divided into two streams, flowing towards the outer bypass duct and the compressor 2 respectively. The air flow flowing towards the compressor 2 is further compressed and enters the main combustion chamber 3. In the main combustion chamber 3, it is mixed with fuel and burned to generate high-temperature gas. This high-temperature gas enters the high-pressure turbine 4 to expand and do work, driving the compressor 2 through the high-pressure shaft. After expanding and doing work, the temperature of the high-temperature gas decreases and enters the mixing chamber 5, where it is mixed with the low-temperature air from the outer bypass duct. Then it enters the inter-stage combustion chamber 6, where it is further mixed with fuel and burned to generate high-temperature gas. This high-temperature gas enters the low-pressure turbine 7 to expand and do work, driving the fan 1 through the low-pressure shaft. After expanding and doing work, the temperature of the high-temperature gas decreases, and after expanding through the nozzle 9, it is ejected to generate thrust.

[0042] The supersonic cruise engine with an inter-stage combustion chamber disclosed in the above embodiment adopts an inter-stage combustion chamber scheme with outer bypass air oxygen supplementation to increase thrust. The temperature rise of the engine is achieved by distributing it to two combustion chambers. Under the same thermal efficiency, it can significantly reduce the temperature of the main combustion chamber, thereby reducing the design difficulty and service life of the engine, and will not significantly increase the size and weight of the engine, and can reduce the pollutant emissions of the engine. In addition, it can maintain a low fuel consumption rate. In practical applications, the temperatures of the main combustion chamber and the inter-stage combustion chamber can be controlled at about 1350K, which can meet the thrust requirements of supersonic cruise, and the fuel consumption rate can be reduced by about 40%.

[0043] In the supersonic cruise engine with an inter-stage combustion chamber disclosed in the above embodiment, the designed fan 1 adopts a FLADE fan. The FLADE fan includes an inner bypass fan and an outer bypass FLADE. Through the design of the number of rotating and stationary stages of the inner bypass fan and the outer bypass FLADE, the pressure of the outer bypass air can be matched with the outlet pressure of the high-pressure turbine 4, enabling the low-temperature air from the outer bypass duct to be well mixed with the high-temperature gas discharged from the low-pressure turbine 7 in the mixing chamber 5, avoiding engine vibration, increasing the surge margin of the engine, supporting the inter-stage combustion chamber 6 to achieve a higher temperature rise and combustion efficiency, and providing a cold source for the cooling of the inter-stage combustion chamber 6 and the low-pressure turbine 7.

[0044] For the FLADE fan, the number of inner bypass fan stages can be matched according to the requirements of the inner bypass pressure ratio of the fan and the load level of a single-stage fan. According to the outlet pressure of the high-pressure turbine, the pressure ratio of the outer bypass duct can be matched, and then the number of outer bypass FLADE stages can be determined. Since the pressure ratio of the outer bypass duct is higher than the inner bypass pressure ratio of the fan, more outer bypass FLADE stages need to be designed than the inner bypass fan stages. In this case, tandem blades can be used to increase the number of outer bypass FLADE stages.

[0045] In the supersonic cruise engine with an inter-turbine combustor disclosed in the above embodiments, since the number of FLADE stages of the FLADE fan is more than that of the core fan, when the Mach number increases, the ratio of the outer flow air pressure to the outlet pressure of the high-pressure turbine 4 will increase, usually from 1.0 to 1.2. At this time, the ejector valve 9 can be opened wider to increase the flow area of the outer flow path, so as to correspondingly reduce the outer flow air pressure and balance the outer flow air pressure with the outlet pressure of the high-pressure turbine 4. Furthermore, the low-temperature air from the outer flow path can be well mixed with the high-temperature gas discharged from the low-pressure turbine 7 in the mixing chamber 5, avoiding engine vibration, improving the surge margin of the engine, supporting the inter-turbine combustor 6 to achieve higher temperature rise and combustion efficiency, and providing a cold source for the cooling of the inter-turbine combustor 6 and the low-pressure turbine 7.

[0046] In the supersonic cruise engine with an inter-turbine combustor disclosed in the above embodiments, when the Mach number decreases, the ejector valve 9 can be closed to reduce the flow area of the outer flow path, so as to correspondingly increase the outer flow air pressure and balance the outer flow air pressure with the outlet pressure of the high-pressure turbine 4. Furthermore, the low-temperature air from the outer flow path can be well mixed with the high-temperature gas discharged from the low-pressure turbine 7 in the mixing chamber 5, avoiding engine vibration, improving the surge margin of the engine, supporting the inter-turbine combustor 6 to achieve higher temperature rise and combustion efficiency, and providing a cold source for the cooling of the inter-turbine combustor 6 and the low-pressure turbine 7.

[0047] In some alternative embodiments, in the above supersonic cruise engine with an inter-turbine combustor, the inter-turbine combustor 6 adopts a hydrogen combustion chamber and uses hydrogen as fuel, which can reduce carbon emissions. In addition, the low calorific value of hydrogen fuel is 2.8 times that of fuel oil, and less hydrogen is required to generate the same amount of heat. Thus, the fuel consumption rate of the engine can be significantly reduced, and it has a high work capacity, which can enable the engine to generate a large thrust, meet the requirements of long-time supersonic cruise, and can improve the work capacity of the low-pressure turbine 7. Furthermore, the work capacity of the high-pressure turbine 4 can be correspondingly reduced, the service life of the high-pressure turbine 4 can be extended, and the requirement for the gas temperature in front of the high-pressure turbine 4 can be reduced, reducing the design difficulty of the high-pressure turbine 4. Moreover, reducing the requirement for the gas temperature in front of the high-pressure turbine 4 means reducing the requirement for the outlet temperature of the main combustor 3, which can reduce the fuel consumption and the temperature in the main combustion zone of the main combustor 3, thereby significantly reducing the carbon emissions of the engine.

[0048] In some alternative embodiments, in the above-described turbine inter-stage combustion chamber supersonic cruise engine, the inter-stage combustion chamber 6 adopts a micro-mixed non-premixed diffusion combustion technology, and can use hundreds or thousands of micro fuel injection devices for lean combustion to achieve low emissions of combustion NOx. Since the diameter of each injection hole is very small, which can be 0.5 mm, there is a large amount of air around the hydrogen fuel jet, and the vast majority of the main combustion zone burns in a lean state. Combined with the inter-stage combustion technology, it can effectively ensure the control of low NOx emissions and at the same time have high flame stability.

[0049] On the other hand, a method for controlling a turbine inter-stage combustion chamber supersonic cruise engine is provided to control the above-described turbine inter-stage combustion chamber supersonic cruise engine, which is characterized by including:

[0050] When the Mach number increases, open the ejector valve 9 and adjust to balance the outer flow air pressure with the outlet pressure of the high-pressure turbine 4;

[0051] When the Mach number decreases, close the ejector valve 9 and adjust to balance the outer flow air pressure with the outlet pressure of the high-pressure turbine 4.

[0052] For the method for controlling a turbine inter-stage combustion chamber supersonic cruise engine disclosed in the above embodiments to control the above-described turbine inter-stage combustion chamber supersonic cruise engine, the description is relatively simple. For specific relevant parts, reference can be made to the relevant descriptions in the part of the turbine inter-stage combustion chamber supersonic cruise engine, and its technical effects can also be referred to the technical effects of the relevant parts of the turbine inter-stage combustion chamber supersonic cruise engine, which will not be elaborated here.

[0053] The various embodiments in the specification are described in a progressive manner. Each embodiment focuses on the differences from other embodiments. The same or similar parts among the various embodiments can be referred to each other. Without conflict, the embodiments and the technical features in the embodiments in the present application can be combined with each other to obtain new embodiments.

[0054] So far, the technical solutions of the present application have been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principle of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present application.

Claims

1. A supersonic cruise engine for an inter-turbine combustion chamber, characterized in that, Comprising: A fan (1), using a FLADE fan; A compressor (2), arranged behind the fan (1); A main combustion chamber (3), arranged behind the compressor (2); A high-pressure turbine (4), arranged behind the main combustion chamber (3) and connected to the compressor (2) through a high-pressure shaft; A mixing chamber (5), arranged behind the high-pressure turbine (4) and connected to the fan (1) through an outer bypass duct; An inter-stage combustion chamber (6), arranged behind the mixing chamber (5); A low-pressure turbine (7), arranged behind the combustion chamber (6) and connected to the fan (1) through a low-pressure shaft; An ejector valve (9), arranged behind the high-pressure turbine (4). When it is opened wide, it deflects towards the inner flow path surface of the outer bypass duct. When it is closed, it deflects towards the outer flow path surface of the outer bypass duct.

2. The supersonic cruise engine with an inter-stage combustion chamber of the turbine according to claim 1, characterized in that: It further comprises: A nozzle (8), arranged behind the low-pressure turbine (7).

3. The supersonic cruise engine with an inter-stage combustion chamber of the turbine according to claim 1, characterized in that: The inter-stage combustion chamber (6) uses a hydrogen combustion chamber.

4. The supersonic cruise engine with an inter-stage combustion chamber of the turbine according to claim 3, characterized in that: The inter-stage combustion chamber (6) uses a micro-mixing non-premixed diffusion combustion technology.

5. A control method for a supersonic cruise engine with an inter-turbine combustion chamber, used to control the supersonic cruise engine with an inter-turbine combustion chamber according to any one of claims 1-4, characterized in that, Comprising: When the Mach number increases, open the ejector valve (9) and adjust to balance the outer bypass air pressure with the outlet pressure of the high-pressure turbine (4); When the Mach number decreases, close the ejector valve (9) and adjust to balance the outer bypass air pressure with the outlet pressure of the high-pressure turbine (4).

Images