Gas generator turbine power device with flow adjustable in large range

Abstract

The invention relates to the technical field of turbine power, in particular to a large-range flow adjustable gas generator turbine power device which comprises a storage tank, a first gas generator and a second gas generator, the first gas generator and the second gas generator are mounted on the two sides of the storage tank respectively, and a turbine power mechanism is arranged behind the first gas generator and the second gas generator. The turbine power mechanism comprises turbine guide vanes and turbine movable vanes which are arranged behind the first fuel gas generator and the second fuel gas generator, a first outlet pipe fixedly arranged at the output end of the first fuel gas generator, and a second outlet pipe fixedly arranged at the output end of the second fuel gas generator. The adjustable range of the local air inlet flow area of the turbine under different working conditions is wider, the working flow range of the turbine is effectively widened, the turbine is better suitable for more operation working conditions, the cruise duration under the condition of the same mass of fuel is prolonged, the economical efficiency of the generator fuel is improved, and the service life of the generator is prolonged. The situation that the turbine flow adjusting range is affected due to the fact that the same through-flow area is adopted for all working conditions of a turbine in a traditional design is avoided.

Description

Technical Field

[0001] The invention relates to the technical field of turbine power, and in particular to a gas generator turbine power device with a wide range of adjustable flow. Background Art

[0002] Air turbine rocket engines mainly use independent gas generators, which do not require air from the compressor to enter and burn. They carry their own energetic fuel medium for catalytic cracking to produce high-temperature combustion gas, which drives the turbine to work, and further drives the compressor to inhale air from the atmosphere. The air inhaled by the compressor is mixed with the combustion gas from the turbine to enter the thrust chamber to generate thrust. In existing air turbine rocket engines, generally one turbine is equipped with one gas generator, or one turbine is equipped with several gas generators, and the gases from the gas generators are mixed and then enter the turbine to work. However, the flow rate of this turbine power unit is small, and it cannot be well applied to more operating conditions, resulting in a shorter cruising time and poor economy under the same quality of fuel. Summary of the invention

[0003] In order to overcome the shortcomings of the prior art, the present invention provides a gas generator turbine power unit with a wide range of adjustable flow. By combining two modular gas generators with a turbine local air intake structure, efficient matching of turbine flow and turbine flow area is achieved, so that the turbine flow can be adjusted over a wide range, solving the problem in the prior art that the turbine flow area is fixed, resulting in a narrow operating range of the turbine flow and inability to always work efficiently.

[0004] In order to solve the above technical problems, the present invention provides the following technical solutions:

[0005] A gas generator turbine power device with a wide range of adjustable flow, comprising a storage tank and a gas generator 1 and a gas generator 2 respectively installed on both sides of the storage tank, wherein a turbine power mechanism is arranged behind the gas generator 1 and the gas generator 2, and the turbine power mechanism comprises turbine guide vanes and turbine moving blades arranged behind the gas generator 1 and the gas generator 2, a first outlet pipe fixedly arranged at the output end of the gas generator 1, and a second outlet pipe fixedly arranged at the output end of the gas generator 2, wherein a first turbine local air intake first stage guide vane 1 is arranged at one end of the first outlet pipe, and a second turbine local air intake first stage guide vane 2 is arranged at one end of the second outlet pipe.

[0006] As a further optimization scheme of the present invention, a turbine first-stage moving blade is arranged on one side of the turbine local air intake first-stage guide vane, and a turbine second-stage moving blade and a turbine third-stage moving blade are arranged in sequence and at intervals on one side of the turbine first-stage moving blade.

[0007] As a further optimization solution of the present invention, a turbine second-stage guide vane is arranged between the turbine first-stage moving blades and the turbine second-stage moving blades.

[0008] As a further optimization solution of the present invention, a turbine third-stage guide vane is arranged between the turbine second-stage moving blades and the turbine third-stage moving blades.

[0009] As a further optimization scheme of the present invention, the gas outlet end of the storage tank is fixedly connected to two pipes, and one end of the two pipes is fixedly connected to the first gas generator and the second gas generator respectively.

[0010] As a further optimization solution of the present invention, a valve 1 is provided at the input end of the gas generator 1, and the valve 1 is fixedly connected to a pipeline installed at the end of the gas generator 1.

[0011] As a further optimization solution of the present invention, a second valve is provided at the input end of the second gas generator, and the second valve is fixedly connected to a pipeline installed at the second end of the gas generator.

[0012] By means of the above technical solution, the present invention provides a gas generator turbine power device with a wide range of adjustable flow, which has at least the following beneficial effects compared with the prior art:

[0013] 1. The present invention combines a modularly designed gas generator with multiple groups of turbine local air intake structures, so that the adjustable range of the turbine local air intake flow area is wider under different working conditions, which can effectively broaden the flow range of the turbine operation, better adapt to more operating conditions, and increase the cruising time under the same quality of fuel, avoiding the situation in traditional designs where the turbine usually uses the same flow area for all working conditions and affects the turbine flow adjustment range.

[0014] 2. In the present invention, under the same turbine output power condition in cruising conditions, the flow rate consumed by the turbine is smaller, which can further extend the flight time of the aircraft, or on the other hand reduce the weight of the aircraft and improve the fuel economy of the gas generator. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0016] Figure 1 It is a schematic diagram of the planar structure of the present invention;

[0017] Figure 2 It is a schematic diagram of the local structure of the present invention.

[0018] In the figure: 1. storage tank; 2. valve one; 3. valve two; 4. gas generator one; 5. gas generator two; 6. first outlet pipe; 7. second outlet pipe; 8. turbine local air intake first stage guide vane one; 9. turbine local air intake first stage guide vane two; 10. turbine first stage moving blades; 11. turbine second stage guide vanes; 12. turbine second stage moving blades; 13. turbine third stage guide vanes; 14. turbine third stage moving blades. DETAILED DESCRIPTION

[0019] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] With the advancement and development of science and technology, the strategic significance of near-space aircraft is becoming increasingly important, requiring them to have long-term cruising capabilities and rapid maneuverability. The core of near-space aircraft is the power system, and the air turbine rocket engine is one of the power systems. Its main features are: it uses an independent gas generator and does not require the air from the compressor to enter it for combustion. It carries its own energetic fuel working fluid for catalytic cracking to produce high-temperature combustion gas, thereby driving the turbine to do work, and further driving the compressor to inhale air from the atmosphere. The air inhaled by the compressor and the combustion gas from the turbine that has done work are mixed into the thrust chamber to generate thrust.

[0021] For air turbine rocket engines, the turbine flow rate required in cruise conditions is small, and the turbine flow rate required in rapid maneuvering conditions is large. This requires that the turbine flow rate has a large adjustment capability. Traditionally, one turbine is usually equipped with one gas generator, or one turbine is equipped with several gas generators. The gases of the gas generators are mixed and then uniformly enter the turbine to do work. However, this method will narrow the adjustable flow range of the turbine power unit. In order to make the adjustable range of the local intake flow area of ​​the turbine wider under different working conditions, the flow range of the turbine operation can be effectively broadened to better adapt to more operating conditions. Refer to Figure 1 - Figure 2 The present embodiment provides a gas generator turbine power device with a wide range of adjustable flow, which is composed of a storage tank 1, a gas generator 1 4, a gas generator 2 5 and a turbine power mechanism. The gas generator 1 4 and the gas generator 2 5 are respectively installed on both sides of the storage tank 1, and the turbine power mechanism is arranged behind the gas generator 1 4 and the gas generator 2 5.

[0022] The number of gas generators can be set to 2 or more, and the specific number of gas generators can be implemented according to the specific situation. This article further explains it through gas generator 1 4 and gas generator 2 5. The operation of each gas generator is independently controlled by a separate valve, and can work separately or simultaneously. In the cruise condition, one gas generator is turned on, and in the fast maneuvering condition, two gas generators work at the same time. Since each gas generator only corresponds to a part of the turbine intake area, the local intake flow area of ​​the turbine is small in the cruise condition, and the gas generator flow consumed is small. In the fast maneuvering condition, the local intake flow area of ​​the turbine is large, and the gas generator flow consumed is large. Through the modular design of the gas generator, the local intake flow area of ​​the turbine is adjustable, so that the turbine flow adjustment range is further increased.

[0023] The outlets of different gas generators are connected to the corresponding local intake turbine first-stage guide vanes through pipelines. Each gas generator corresponds to only a part of the turbine intake area. The high-temperature gases generated by different gas generators enter the corresponding turbine local intake first-stage guide vane 1 8 or turbine local intake first-stage guide vane 2 9 through different pipelines, and then enter the subsequent turbine first-stage moving blades 10, turbine second-stage guide vanes 11, turbine second-stage moving blades 12, turbine third-stage guide vanes 13, turbine third-stage moving blades 14 and other turbine components to perform work.

[0024] The outlet end of the storage tank 1 is fixedly connected with two pipelines, and the other ends of the two pipelines are fixedly connected with the gas generator 14 and the gas generator 25, respectively. The input end of the gas generator 14 is provided with a valve 12, and the valve 12 is fixedly connected with the pipeline installed at the end of the gas generator 14. The input end of the gas generator 25 is provided with a valve 23, and the valve 23 is fixedly connected with the pipeline installed at the end of the gas generator 25. The storage tank 1 carries its own energetic fuel working medium, which can enter the gas generator 14 and the gas generator 25 for catalytic cracking to produce high-temperature fuel gas after passing through the valve 12 and the valve 23 respectively. When the engine is working, the gas generator 14 flow is controlled separately by the valve 12, and the gas generator 25 flow is controlled separately by the valve 23, and can work independently.

[0025] The turbine power mechanism includes turbine disc guide vanes and turbine moving blades arranged after gas generator 1 4 and gas generator 2 5, a first outlet pipe 6 fixedly arranged at the output end of gas generator 1 4, and a second outlet pipe 7 fixedly arranged at the output end of gas generator 2 5, one end of the first outlet pipe 6 is provided with a turbine local air intake first stage guide vane 1 8, and one end of the second outlet pipe 7 is provided with a turbine local air intake first stage guide vane 2 9.

[0026] like Figure 2As shown by the middle arrow, the gas generator 14 is separately connected to the first outlet pipe 6, and further connected to the turbine local air intake first stage guide vane 18 separately. The high-temperature combustion gas generated from the gas generator 14 enters the turbine local air intake first stage guide vane 18 only through the first outlet pipe 6. In order to prevent the local air intake of the turbine from generating unbalanced excitation on the turbine blades and thus causing large vibration of the rotor, the combustion gas coming out of the first outlet pipe 6 is divided into two and enters two 180° symmetrical turbine local air intake first stage guide vanes 18; the gas generator 25 is separately connected to the second outlet pipe 7, and further connected to the turbine local air intake first stage guide vane 29. Similarly, the high-temperature combustion gas generated from the gas generator 25, as shown in FIG. Figure 2 As shown by the middle arrow, after passing through the second outlet pipe 7, it is split into two and only enters two turbine local intake first-stage guide vanes 9 that are 180° symmetrical.

[0027] A turbine first-stage moving blade 10 is arranged on one side of the turbine local air intake first-stage guide vane 8, and a turbine second-stage moving blade 12 and a turbine third-stage moving blade 14 are arranged in sequence on one side of the turbine first-stage moving blade 10. A turbine second-stage guide vane 11 is arranged between the turbine first-stage moving blade 10 and the turbine second-stage moving blade 12, and a turbine third-stage guide vane 13 is arranged between the turbine second-stage moving blade 12 and the turbine third-stage moving blade 14.

[0028] Therefore, in the cruise condition, only valve 12 is opened, and the gas generator 14 channel is working. At this time, only the turbine local intake first stage guide vane 18 has gas flowing into the subsequent turbine first stage moving blade 10, turbine second stage guide vane 11, turbine second stage moving blade 12, turbine third stage guide vane 13, turbine third stage moving blade 14, while no gas flows through the turbine local intake first stage guide vane 29. It can be seen from the following two formulas that in the turbine flow rate m t Under the same conditions, due to the reduction of the flow area A of the turbine gas t , so it is necessary to increase the turbine inlet pressure P 1t , therefore, the turbine output power will increase. For cruise conditions, the power consumption at the compressor end is certain, and the required turbine output power is also certain, which means that the flow consumed by the turbine is reduced.

[0029] Turbine flow:

[0030] Turbine output power:

[0031] In the maneuvering acceleration condition, valve 1 2 and valve 2 3 are all opened, the channels of gas generator 1 4 and gas generator 2 5 are all opened, and the gas passes through the turbine local air intake first stage guide vane 1 8 and the turbine local air intake first stage guide vane 2 9 to enter the subsequent turbine components to perform work. The substantial increase in the flow area causes the turbine flow rate to increase accordingly to meet the requirements of the aircraft's maneuvering acceleration.

[0032] The flow area of ​​the turbine local air intake first stage guide vane 1 8 and the turbine local air intake first stage guide vane 2 9 can be different. The flow area of ​​the turbine local air intake first stage guide vane 1 8 is as small as possible, and the flow area of ​​the turbine local air intake first stage guide vane 2 9 is as large as possible to achieve a larger range of flow regulation requirements.

[0033] The present invention modularizes the gas generator and the local intake turbine, opens different gas generator passages under different working conditions to adjust the flow area of ​​the turbine gas, so that the turbine can always work efficiently during a wide range of flow changes, and the flow change range can reach 10 times or even higher, which broadens the working range of the engine. At the same time, when the aircraft is cruising, the use of a small flow area reduces the flow consumed by the gas generator, which increases the cruising time of the aircraft. From another perspective, it can reduce the weight of the aircraft and improve the fuel economy of the gas generator.

[0034] It should be noted that, in this article, the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0035] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A gas generator turbine power device with a wide range of adjustable flow, comprising a storage tank (1) and a gas generator 1 (4) and a gas generator 2 (5) respectively mounted on both sides of the storage tank (1), characterized in that: A turbine power mechanism is arranged behind the gas generator 1 (4) and the gas generator 2 (5); The turbine power mechanism comprises turbine guide vanes and turbine moving blades arranged after the first gas generator (4) and the second gas generator (5), a first outlet pipe (6) fixedly arranged at the output end of the first gas generator (4), and a second outlet pipe (7) fixedly arranged at the output end of the second gas generator (5), one end of the first outlet pipe (6) is provided with a first-stage guide vane (8) for local air intake of the turbine, and one end of the second outlet pipe (7) is provided with a second-stage guide vane (9) for local air intake of the turbine.

2. A gas generator turbine power device with a wide range of adjustable flow according to claim 1, characterized in that: A turbine first-stage moving blade (10) is arranged on one side of the turbine local air intake first-stage guide vane (8), and a turbine second-stage moving blade (12) and a turbine third-stage moving blade (14) are arranged in sequence and at intervals on one side of the turbine first-stage moving blade (10).

3. A gas generator turbine power device with a wide range of adjustable flow according to claim 2, characterized in that: A turbine second-stage guide vane (11) is arranged between the turbine first-stage moving blade (10) and the turbine second-stage moving blade (12).

4. A gas generator turbine power device with a wide range of adjustable flow according to claim 2, characterized in that: A turbine third-stage guide vane (13) is arranged between the turbine second-stage moving blade (12) and the turbine third-stage moving blade (14).

5. A gas generator turbine power device with a wide range of adjustable flow according to claim 1, characterized in that: The outlet end of the storage tank (1) is fixedly connected to two pipelines, and one end of the two pipelines is fixedly connected to the gas generator 1 (4) and the gas generator 2 (5) respectively.

6. A gas generator turbine power device with a wide range of adjustable flow according to claim 5, characterized in that: The input end of the gas generator 1 (4) is provided with a valve 1 (2), and the valve 1 (2) is fixedly connected to a pipeline installed at the end of the gas generator 1 (4).

7. A gas generator turbine power device with a wide range of adjustable flow rate according to claim 5, characterized in that: The input end of the second gas generator (5) is provided with a second valve (3), and the second valve (3) is fixedly connected to a pipeline installed at the end of the second gas generator (5).

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