Multi-pipeline local air inlet turbine with differential design of stationary blades

Abstract

The invention relates to the technical field of engine turbines, in particular to a multi-pipeline local air inlet turbine with differentiated stationary blades, which comprises two symmetrically arranged air inlet branches I, two symmetrically arranged air inlet branches II and a turbine assembly for adapting to a wide-range operation condition, the turbine stage number of the turbine assembly comprises but is not limited to three stages, and the turbine assembly comprises first-stage turbine stationary blades I arranged on the paths of the two first air inlet branches correspondingly and first-stage turbine stationary blades II arranged on the paths of the two second air inlet branches correspondingly. Stationary blade types matched with the airflow angle of the current working condition can be adopted under different working conditions, the airflow attack angle can be greatly reduced, and therefore the turbine efficiency is improved, the turbine can adapt to more operation working conditions, the application range of the air inlet turbine is widened, and the service life of the turbine is prolonged. The situation that an existing air inlet turbine needs to select the air inlet degree to be matched with the turbine flow, so that the turbine blade profile cannot adapt to the wide-range operation working condition is avoided, fuel consumption of the flight cycle of an aircraft is reduced, and economical efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the field of engine turbine technology, and in particular to a multi-pipeline local air intake turbine with differentiated stator blade design. Background Art

[0002] The application of local intake turbines in air turbine rocket engines is very suitable for the design requirements of small flow and large pressure drop ratio. Conventional local intake turbine designs usually adopt the idea of ​​full-circle intake to design turbine blades, and then select appropriate local intake degrees to match the turbine flow. The blades of the same stage of turbine stators are the same, which makes the turbine blades unable to adapt to a wide range of operating conditions. This causes the turbine to have a large airflow attack angle when operating under non-design conditions, resulting in increased losses and reduced efficiency. It is not very suitable for aircraft engines with wide-range flight requirements, which affects the scope of application of local intake turbines. Summary of the invention

[0003] In order to overcome the shortcomings of the prior art, the present invention provides a multi-pipeline local intake turbine with differentiated stator blade designs, which solves the problem that the prior art selects local air intake to match the turbine flow to obtain turbine stator blades of the same stage with the same blade shape, making the turbine blade shape unable to adapt to a wider range of operating conditions.

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

[0005] A multi-pipe local intake turbine with a differentiated stator blade design, comprising two symmetrically arranged intake branch one and two symmetrically arranged intake branch two and a turbine assembly for adapting to a wider range of operating conditions, wherein the number of turbine stages of the turbine assembly includes but is not limited to three stages, and the turbine assembly comprises a first-stage turbine stator blade one respectively arranged on two intake branch one paths, and a first-stage turbine stator blade two respectively arranged on two intake branch two paths, a second-stage turbine stator blade one is arranged at intervals on one side of the first-stage turbine stator blade one, a first-stage turbine moving blade is arranged between the first-stage turbine stator blade one and the second-stage turbine stator blade one, a second-stage turbine stator blade two is arranged at intervals on one side of the first-stage turbine stator blade two, and the first-stage turbine moving blade is located between the first-stage turbine stator blade two and the second-stage turbine stator blade two.

[0006] As a further optimization scheme of the present invention, a turbine third-stage stator blade one is disposed at intervals on one side of the turbine second-stage stator blade one, and a turbine third-stage stator blade two is disposed at intervals on one side of the turbine second-stage stator blade two.

[0007] As a further optimization scheme of the present invention, a turbine second-stage moving blade is disposed at intervals on one side of the turbine first-stage moving blade, and a turbine third-stage moving blade is disposed at intervals on one side of the turbine second-stage moving blade.

[0008] As a further optimization scheme of the present invention, the turbine second stage stator blade one and the turbine second stage stator blade two are both located between the turbine first stage moving blades and the turbine second stage moving blades, and the turbine third stage stator blade one and the turbine third stage stator blade two are both located 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 inlet angle direction of the first-stage stator blade one of the turbine and the first-stage stator blade two of the turbine are the same, the outlet angle direction one of the first-stage stator blade one of the turbine corresponds to the low-speed operating condition, and the outlet angle direction two of the first-stage stator blade two of the turbine corresponds to the high-speed operating condition.

[0010] As a further optimization scheme of the present invention, the inlet and outlet velocity triangles of the turbine second-stage stator blade 1 and the turbine second-stage stator blade 2 will change with the rotation speed.

[0011] As a further optimization scheme of the present invention, the inlet angle direction one and the outlet angle direction three of the second-stage stator blade one of the turbine are used for low-speed working conditions, and the inlet angle direction two and the outlet angle direction four of the second-stage stator blade two of the turbine are used for high-speed working conditions.

[0012] As a further optimization scheme of the present invention, the inlet and outlet velocity triangles of the turbine third-stage stator blade one and the turbine third-stage stator blade two will change with the rotational speed.

[0013] As a further optimization scheme of the present invention, the inlet angle direction three and the outlet angle direction five of the third-stage stator blade one of the turbine are used for low-speed working conditions, and the inlet angle direction four and the outlet angle direction six of the third-stage stator blade two of the turbine are used for high-speed working conditions.

[0014] By means of the above technical solution, the present invention provides a multi-pipe local intake turbine with differentiated stator blade design, which has at least the following beneficial effects compared with the prior art:

[0015] 1. The present invention differentiates the inlet angle and outlet angle of the stator blades of the turbine multi-pipe local air intake, which is conducive to using the stator blade shape that matches the airflow angle of the current working condition under different working conditions, and can greatly reduce the airflow attack angle, thereby improving the turbine efficiency, being able to adapt to more operating conditions, and expanding the application range of the intake turbine, avoiding the situation in which the existing intake turbine needs to select the intake degree to match the turbine flow, making the turbine blade shape unable to adapt to a wider range of operating conditions.

[0016] 2. In the present invention, the rotation speed, inlet angle and outlet angle of the turbine multi-stage stationary blades and moving blades can be adaptively matched under low-speed and high-speed operating conditions, and can be adjusted according to the actual operating conditions of the aircraft, thereby avoiding energy waste caused by using a large flow rate under low-speed conditions required by the aircraft, reducing the fuel consumption of the aircraft during the flight cycle, improving the thrust-to-weight ratio of the turbine engine, and improving the economy of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] 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:

[0018] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0019] Figure 2 It is a schematic diagram of the working state of the first-stage stationary blade of the turbine of the present invention;

[0020] Figure 3 It is a schematic diagram of the working state of the second stage stator blade of the turbine of the present invention;

[0021] Figure 4 It is a schematic diagram of the working state of the third stage stator blade of the turbine of the present invention.

[0022] In the figure: 1. Intake branch one; 2. Intake branch two; 3. Turbine first-stage stator blade one; 4. Turbine first-stage stator blade two; 5. Turbine first-stage moving blade; 6. Turbine second-stage stator blade one; 7. Turbine second-stage stator blade two; 8. Turbine second-stage moving blade; 9. Turbine third-stage stator blade one; 10. Turbine third-stage stator blade two; 11. Turbine third-stage moving blade; 13. Exhaust angle direction one; 14. Exhaust angle direction two; 15. Intake angle direction one; 16. Intake angle direction two; 17. Exhaust angle direction three; 18. Exhaust angle direction four; 19. Intake angle direction three; 20. Exhaust angle direction five; 21. Intake angle direction four; 22. Exhaust angle direction six. DETAILED DESCRIPTION

[0023] 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.

[0024] The local intake turbine is applied to the turbine structure under the design requirements of small flow rate. It can mainly solve the problem of the sharp increase in secondary flow loss and the difficulty of processing and manufacturing caused by the small height of the turbine blades under the condition of small flow rate. The application scenarios are very wide. The application of local intake turbine in air turbine rocket engine is very suitable for the design requirements of small flow rate and large pressure drop ratio. The efficiency of the local intake turbine in using the energy of high temperature and high pressure combustion gas is the turbine efficiency, which is an important indicator of the economy of turbine engine. High turbine efficiency means that the same output power consumes less fuel. For aircraft, a complete flight cycle can carry less fuel, thereby improving thrust-to-weight ratio and economy.

[0025] At present, the turbine blade shape is usually designed with the idea of ​​full-circle air intake, and then the appropriate local air intake degree is selected to match the turbine flow rate. The blade shape of the same-stage turbine stator is the same. Because different operating conditions require different turbine flow rates, but the existing turbine blade shape cannot adapt to a wide range of operating conditions, it causes the turbine to have a large airflow angle when operating under non-design conditions, which increases losses and reduces efficiency. In order to use a stator blade shape that matches the current airflow angle under different operating conditions, the airflow angle can be greatly reduced, thereby improving turbine efficiency. Figure 1 - Figure 4 This embodiment provides a multi-pipe local intake turbine with a differentiated stator blade design, including two symmetrically arranged intake branches 1 and two symmetrically arranged intake branches 2 and a turbine assembly for adapting to a wider range of operating conditions, wherein the number of turbine stages of the turbine assembly includes but is not limited to three stages.

[0026] The local air intake turbine of the present invention is installed in the turbine casing, and the air intake branch 1 and the air intake branch 2 are both connected to the air intake pipe. The air intake branch 1 and the air intake branch 2 are respectively provided with independent valves for control. According to actual needs, the air intake branch 1 or the air intake branch 2 can be opened separately, or the air intake branch 1 and the air intake branch 2 can be opened at the same time.

[0027] The turbine assembly includes a turbine first-stage stator blade 1 3 respectively arranged on two intake branch 1 paths, and a turbine first-stage stator blade 2 4 respectively arranged on two intake branch 2 paths, a turbine second-stage stator blade 6 is arranged at one side of the turbine first-stage stator blade 3, a turbine first-stage moving blade 5 is arranged between the turbine first-stage stator blade 3 and the turbine second-stage stator blade 6, a turbine second-stage stator blade 2 7 is arranged at one side of the turbine first-stage stator blade 2 4, and the turbine first-stage moving blade 5 is located between the turbine first-stage stator blade 2 4 and the turbine second-stage stator blade 2 7.

[0028] Furthermore, a turbine third-stage stator blade 1 9 is interspersed on one side of the turbine second-stage stator blade 1 6, a turbine third-stage stator blade 2 10 is interspersed on one side of the turbine second-stage stator blade 2 7, a turbine second-stage moving blade 8 is interspersed on one side of the turbine first-stage moving blade 5, and the turbine second-stage stator blade 1 6 and the turbine second-stage stator blade 2 7 are both located between the turbine first-stage moving blade 5 and the turbine second-stage moving blade 8, a turbine third-stage moving blade 11 is interspersed on one side of the turbine second-stage moving blade 8, and the turbine third-stage stator blade 1 9 and the turbine third-stage stator blade 2 10 are both located between the turbine second-stage moving blade 8 and the turbine third-stage moving blade 11.

[0029] Among them, a turbine shaft is also rotatably arranged in the turbine casing, and the first-stage turbine blades 5, the second-stage turbine blades 8 and the third-stage turbine blades 11 are fixedly installed on the turbine shaft of the turbine casing at intervals in sequence, and the first-stage turbine blades 3, the second-stage turbine blades 6 and the third-stage turbine blades 9 are fixedly installed in the turbine casing at intervals in sequence, and the first-stage turbine blades 4, the second-stage turbine blades 7 and the third-stage turbine blades 10 are fixedly installed in the turbine casing at intervals in sequence, which can ensure that the turbine blades rotate more stably and it is also more convenient to adjust the turbine flow range according to needs.

[0030] The design of the first-stage turbine stator blades is that the inlet angle directions of the turbine first-stage stator blade 1 3 and the turbine first-stage stator blade 2 4 are the same. Due to the difference in rotational speed, the stator blade outlet velocity triangle changes with the rotational speed, resulting in different outlet angles of the two branch stator blades. The outlet angle direction 13 of the turbine first-stage stator blade 1 3 corresponds to the low-speed operating condition, and the outlet angle direction 2 14 of the turbine first-stage stator blade 2 4 corresponds to the high-speed operating condition.

[0031] The design of the second-stage turbine stator blades, the inlet and outlet velocity triangles of the turbine second-stage stator blade 1 6 and the turbine second-stage stator blade 2 7 will change with the speed change, the inlet angle direction 15 and the outlet angle direction 17 of the turbine second-stage stator blade 1 6 are used for low-speed conditions, and the inlet angle direction 2 16 and the outlet angle direction 4 18 of the turbine second-stage stator blade 2 7 are used for high-speed conditions.

[0032] The design of the third-stage turbine stator blades, the inlet and outlet velocity triangles of the turbine third-stage stator blade 1 9 and the turbine third-stage stator blade 2 10 will change with the speed change, the inlet angle direction three 19 and the outlet angle direction five 21 of the turbine third-stage stator blade 1 9 are used for low-speed conditions, and the inlet angle direction four 20 and the outlet angle direction six 22 of the turbine third-stage stator blade 2 10 are used for high-speed conditions.

[0033] During use, the present invention can significantly reduce the airflow attack angle by differentially designing the inlet and outlet angles of the stator blades of the turbine multi-pipe local air intake and adopting stator blade shapes that match the airflow angle of the current working conditions under different working conditions, thereby improving the turbine efficiency.

[0034] When the turbine is working at a low speed, only the intake branch 1 is opened, and the intake branch 2 is closed. The airflow follows the route of the intake branch 1, and passes through the turbine first-stage stator 13, the turbine first-stage moving blade 5, the turbine second-stage stator 16, the turbine second-stage moving blade 8, the turbine third-stage stator 19, and the turbine third-stage moving blade 11 in sequence, and drives the turbine shaft to operate at a low speed through the turbine first-stage moving blade 5, the turbine second-stage moving blade 8, and the turbine third-stage moving blade 11; when the turbine is working at a high speed, the intake branch 1 and the intake branch 2 are all opened. In addition to entering the turbine to perform work according to the route of the above-mentioned intake branch 1, the airflow also passes through the route of the intake branch 2, and passes through the turbine first-stage stator 4, the turbine first-stage moving blade 5, the turbine second-stage stator 27, the turbine second-stage moving blade 8, the turbine third-stage stator 210, and the turbine third-stage moving blade 11 in sequence, and drives the turbine shaft to operate at a high speed through the turbine first-stage moving blade 5, the turbine second-stage moving blade 8, and the turbine third-stage moving blade 11.

[0035] 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.

[0036] 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 multi-pipe local air intake turbine with differentiated stator blade design, characterized in that: The invention comprises two symmetrically arranged intake branches one (1) and two symmetrically arranged intake branches two (2) and a turbine assembly adapted to a wider range of operating conditions, wherein the number of turbine stages of the turbine assembly includes but is not limited to three stages; The turbine assembly comprises a turbine first-stage stator blade (3) respectively arranged on two intake branch one (1) paths, and a turbine first-stage stator blade (4) respectively arranged on two intake branch two (2) paths, a turbine second-stage stator blade (6) is arranged at intervals on one side of the turbine first-stage stator blade (3), a turbine first-stage moving blade (5) is arranged between the turbine first-stage stator blade (3) and the turbine second-stage stator blade (6), a turbine second-stage stator blade (7) is arranged at intervals on one side of the turbine first-stage stator blade (4), and the turbine first-stage moving blade (5) is located between the turbine first-stage stator blade (4) and the turbine second-stage stator blade (7).

2. A multi-pipe local intake turbine with differentiated stator blade design according to claim 1, characterized in that: A turbine third-stage stator blade one (9) is arranged at intervals on one side of the turbine second-stage stator blade one (6), and a turbine third-stage stator blade two (10) is arranged at intervals on one side of the turbine second-stage stator blade two (7).

3. The multi-pipe local air intake turbine with differentiated stator blade design according to claim 2, characterized in that: A turbine second-stage moving blade (8) is arranged at intervals on one side of the turbine first-stage moving blade (5), and a turbine third-stage moving blade (11) is arranged at intervals on one side of the turbine second-stage moving blade (8).

4. The multi-pipe local air intake turbine with differentiated stator blade design according to claim 3, characterized in that: The turbine second-stage stator blade one (6) and the turbine second-stage stator blade two (7) are both located between the turbine first-stage moving blade (5) and the turbine second-stage moving blade (8), and the turbine third-stage stator blade one (9) and the turbine third-stage stator blade two (10) are both located between the turbine second-stage moving blade (8) and the turbine third-stage moving blade (11).

5. The multi-pipe local air intake turbine with differentiated stator blade design according to claim 1, characterized in that: The inlet angle direction of the first-stage turbine stator blade one (3) and the first-stage turbine stator blade two (4) is the same, the outlet angle direction one (13) of the first-stage turbine stator blade one (3) corresponds to a low-speed operating condition, and the outlet angle direction two (14) of the first-stage turbine stator blade two (4) corresponds to a high-speed operating condition.

6. The multi-pipe local air intake turbine with differentiated stator blade design according to claim 1, characterized in that: The inlet and outlet speed triangles of the turbine second stage stator blade 1 (6) and the turbine second stage stator blade 2 (7) will change as the rotation speed changes.

7. The multi-pipe local intake turbine with differentiated stator blade design according to claim 1, characterized in that: The inlet angle direction one (15) and the outlet angle direction three (17) of the second-stage stator blade one (6) of the turbine are used for low-speed working conditions, and the inlet angle direction two (16) and the outlet angle direction four (18) of the second-stage stator blade two (7) of the turbine are used for high-speed working conditions.

8. The multi-pipe local air intake turbine with differentiated stator blade design according to claim 2, characterized in that: The inlet and outlet velocity triangles of the turbine third stage stator blade one (9) and the turbine third stage stator blade two (10) will change as the rotation speed changes.

9. A multi-pipe local intake turbine with differentiated stator blade design according to claim 8, characterized in that: The inlet angle direction three (19) and the outlet angle direction five (21) of the third stage stator blade one (9) of the turbine are used for low speed working conditions, and the inlet angle direction four (20) and the outlet angle direction six (22) of the third stage stator blade two (10) of the turbine are used for high speed working conditions.

Images