CN214330752U - Double-side air inlet volute for aviation environment-controlled stamping refrigeration turbine - Google Patents
Double-side air inlet volute for aviation environment-controlled stamping refrigeration turbine Download PDFInfo
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- CN214330752U CN214330752U CN202022841579.8U CN202022841579U CN214330752U CN 214330752 U CN214330752 U CN 214330752U CN 202022841579 U CN202022841579 U CN 202022841579U CN 214330752 U CN214330752 U CN 214330752U
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Abstract
The utility model discloses a bilateral air inlet volute for an aviation environment-controlled stamping refrigeration turbine, which comprises a power turbine arranged in a shell, a nozzle ring correspondingly arranged on the power turbine, a volute inlet arranged on the shell, and an annular flow passage arranged in the shell; the annular flow channel comprises a first volute flow channel and a second volute flow channel which are respectively and symmetrically arranged at two sides of the nozzle ring; fluid working media conveyed through the volute inlet enter a large-section flow channel formed by the volute flow channels on the two sides of the volute flow channel I and the volute flow channel II and then can be decelerated, the diffusion effect is achieved, and therefore a small-flow-speed high-static-pressure area is formed at the nozzle ring inlet. The utility model discloses hollowing out the two spiral case runners that form the nozzle both sides with the inside entity supporting structure of stamping turbine under the condition that satisfies structural strength, increase spiral case runner sectional area under the prerequisite that does not increase the stamping turbine volume, realize the purpose to high-speed ram air speed reduction diffusion, be favorable to the high-efficient work of stamping turbine more, can also alleviate stamping turbine weight simultaneously, reduce the aircraft load.
Description
Technical Field
The utility model relates to a turbo expander and air refrigeration technical field, concretely relates to aviation environmental control punching press refrigeration turbine is with two side spiral cases that admit air.
Background
Military aircraft generally improve tactical performance by additionally hanging a nacelle, and expand airborne functions and performance in the fields of electronic countermeasure, reconnaissance, navigation, guidance and the like. In order to ensure reliable operation of the nacelle electronics, a separate environmental control system must be provided in the nacelle, which typically employs a ram turbine as the core cooling solution.
Ram air generated by airplane flight enters the turbine through the nacelle air inlet channel to drive the refrigeration turbine to rotate at a high speed, enthalpy drop of the working medium is realized, energy released by expansion of the working medium is transferred to the air compressor at the other end in a mechanical work mode through the main shaft, low-pressure air in the cabin is discharged out of the cabin after being pressurized by the compression turbine to form an open cycle, and meanwhile, the suction effect of the air compressor can reduce the pressure in the cabin and improve the expansion ratio and the refrigeration performance of the refrigeration turbine. The ram refrigeration turbine adopts ram air as a power source, so that power consumption is not needed, the refrigeration capacity is increased along with the increase of the Mach number, and the influence of the rise of the aerodynamic thermal load along with the increase of the Mach number can be overcome in a certain range. In order to better meet the requirement of an electronic pod on the continuous increase of the refrigerating capacity, a stamping turbine refrigerating scheme driven by a power turbine is provided, partial stamping air outputs work through additional expansion of the power turbine, the air inlet degree of the refrigerating turbine can be increased, the system can work under the design working condition as much as possible, so that the larger turbine temperature drop and refrigerating capacity are obtained, the problems that the design size of the typical stamping turbine wheel diameter is larger, the working efficiency is low under the non-design working condition and the like can be solved, and the method is a main loop control cooling mode adopted by the pod mainstream at home and abroad.
As shown in fig. 1, the refrigeration turbine and the power turbine are collectively called as a working wheel, and energy conversion can be performed by using the speed change of ram air when flowing in a flow channel of the refrigeration turbine and the power turbine, and external work is output by a working wheel shaft, so that the internal energy and temperature of air at the outlet of the turbine are reduced, and refrigeration is realized. The through-flow part of the working wheel can be divided into four parts of a volute, a nozzle, an impeller and an outlet diffuser according to the sequence of flowing of the airflow. Ram air introduced by a nacelle air inlet is guided by the volute and then distributed to the nozzle ring inlet, generally speaking, no energy conversion exists in gas flowing in the volute except for flow loss, the gas flow guided by the volute is accelerated after passing through a contraction channel or a convergent-divergent channel in the nozzle, primary expansion is realized in the nozzle, partial temperature drop and high speed are obtained, then the impeller is pushed to rotate at high speed, and the output shaft is driven to work, and the expansion and the temperature drop are continued in the nozzle, so that the specific enthalpy and the temperature are further reduced.
Different from a ground application scene, the ram refrigeration turbine driven by aviation ram air has the characteristics of large flow, high inlet air flow speed, low total pressure, high temperature, low density and the like, and in order to ensure that the ram turbine installed in a nacelle has enough air inflow, the pipe diameter of an air inlet of the nacelle is larger than that required by normal air inlet of the turbine, so that the flow loss of high-speed air flow (generally more than mach number 0.65) in the air inlet is compensated, and the high-speed ram air enters a nozzle without diffusion and deceleration, and then flow field disorder, eddy loss increase, insufficient expansion in the nozzle and other factors which are not beneficial to the work of the ram turbine occur, and the refrigeration efficiency of the turbine is influenced. Under the condition of subsonic speed, the cross section and the volume of the air inlet channel need to be increased by utilizing the gradually-expanding air inlet channel to expand the pressure of the air before the air enters the turbine, so that the space of equipment in the cabin is occupied to a great extent, and the work of airborne equipment is not facilitated. Therefore, the mode of increasing the sectional area of the volute can be adopted, and the space in the volute is utilized to realize the speed reduction and diffusion buffering of high-speed airflow. However, for the aviation stamping refrigeration turbine driven by the power turbine, because the power turbine is located in the middle of the casing of the complete turbine and is affected by a middle bearing, a main shaft, a supporting structure and the like, the adoption of the mode of increasing the sectional area of the single-side air inlet volute can increase the volume of the turbine, and also can occupy the space of equipment in the cabin, which is contrary to the strict requirement on the volume and weight of the equipment in the cabin under the condition of aviation.
SUMMERY OF THE UTILITY MODEL
The utility model provides a pair of aviation ring accuse punching press refrigeration turbine is with two side spiral casings that admit air can solve the volume that utilizes intake duct diffuser pipe diffusion to bring and occupy the problem with the turbine volume increase problem that adopts increase unilateral spiral casing sectional area to carry out the diffusion and bring, in order effectively to utilize the punching press turbine inner space simultaneously.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a bilateral air inlet volute for an aviation environment-controlled stamping refrigeration turbine comprises a shell, wherein a power turbine is arranged in the shell, a nozzle ring is correspondingly arranged at an inlet of the power turbine and used for converting the total pressure of a fluid working medium into speed and providing driving torque for the power turbine;
the shell is provided with a volute inlet, and an annular flow passage is arranged in the shell;
the shell is provided with an airflow outlet pipeline, and airflow flows out through the airflow outlet pipeline;
the annular flow channel comprises a first volute flow channel and a second volute flow channel which are respectively and symmetrically arranged at two sides of the nozzle ring;
the volute inlet is connected with the air inlet channel and used for conveying fluid working media, and the fluid working media conveyed through the volute inlet can decelerate after entering a large-section flow channel formed by the volute flow channels on the two sides of the volute flow channel I and the volute flow channel II, so that a diffusion effect is realized, and a small-flow-speed high-static-pressure area is formed at the nozzle ring inlet.
Furthermore, the second volute flow channel is the original volute flow channel of the power turbine, and the second volute flow channel is manufactured into a uniform cross section form in a turning forming mode.
Furthermore, the first volute flow channel is additionally arranged by utilizing an internal supporting structure of the stamping turbine, and is manufactured into a uniform cross section form by adopting a turning forming mode.
Furthermore, the nozzle ring is a rectangular section nozzle manufactured by milling and is arranged in the middle of the volute flow channels on the two sides.
Furthermore, the power turbine is formed by milling, is supported by a high-speed bearing and a rotating shaft to rotate and is arranged at the axle center positions of the nozzle ring, the first volute flow channel and the second volute flow channel.
Furthermore, the nozzle ring and the volute flow channel I are integrally processed.
Further, the first volute flow channel is fastened with the shell through screws.
Furthermore, the volute flow channel II and the shell are connected at a joint in a welding mode.
The utility model provides a two sides spiral case that admits air with diffusion function utilizes the inside bearing structure space of aviation stamping turbine to set up power turbine spiral case runner, uses increase spiral case runner sectional area with former spiral case runner cooperation, plays the speed reduction diffusion effect to turbine entry aviation ram air. Meanwhile, the weight of the stamping turbine can be reduced under the condition of unchanged volume. Specifically, the spaces on two sides of the nozzle in the casing are used as volute flow channels, the flow cross section area in front of the nozzle inlet is increased, and the gas flow is subjected to speed reduction and pressure expansion through the increase of the cross section area and the volume in an approximately heat insulation state to be close to a stagnation state, so that the flow loss of the flow part of the turbine is effectively reduced, the expansion in the nozzle is closer to an ideal state, and the refrigeration efficiency can be greatly improved. Meanwhile, the solid part in the turbine is hollowed into the flow channel under the condition that the structural strength is not influenced, the weight of the turbine can be reduced, and the turbine is more friendly to aviation application.
The utility model discloses utilize topological optimization's mode, utilize the inside nozzle both sides space of stamping turbine casing to set up the runner on the basis of structural strength and processability in guaranteeing the turbine, increase spiral case cross-sectional area and interior volume, carry out speed reduction diffusion to high-speed punching press air current to the realization realizes evenly admitting air of nozzle under less loss of pressure condition, reduces frictional loss and eddy current loss, improves turbine work efficiency.
The utility model discloses inside power turbine driven aviation stamping turbine, the entity structural part design with the both sides of power wheel nozzle is processed into the spiral case runner, and the spiral case form of admitting air is gone up to two sides promptly, is located the nozzle cascade both sides, and this spiral case runner is the relative sealed annular space of connecting inlet pipeline and nozzle, checks spiral case runner sectional area maximize through intensity under the condition of guaranteeing structural strength. Ram air enters the turbine through the air inlet channel and then firstly enters the volute flow channels on the two sides of the nozzle, and continuously flows to the inside of the nozzle from the two sides of the nozzle inlet in the circumferential flow process of the air flow along the volute flow channels. The introduction of the bilateral volute greatly improves the sectional area of the flow channel, so that the airflow speed in the volute with the same flow rate is obviously reduced, the airflow speed can be controlled within 12m/s generally, the traditional volute does not need to be adopted to meet the requirement of axisymmetric exhaust and ensure the constant variable section design of the circumferential airflow speed (generally 15-20m/s) of the inner circle of the volute outlet, and the bilateral volute flow channel can adopt the form of equal sections to reduce the manufacturing difficulty.
According to the above technical scheme, the utility model discloses an aviation environmental control punching press refrigeration turbine is with two side spiral casings that admit air relates to a turbo expander spiral case form, belongs to turbo expander and air refrigeration field, specifically is an utilize nozzle both sides space to carry out the runner of water conservancy diversion and diffusion buffering, can be applied to the turbo expander that adopts the incoming flow air drive work of big tolerance, the big velocity of flow, little static pressure, in the aviation environmental control air conditioning field to requirements such as refrigeration turbine weight load, volume load comparatively harsh occasion suitability higher. The utility model provides a volute form of air inlet, diffusion and flow guiding at two sides of the nozzle, which can effectively utilize the inner space of the ram turbine to carry out high-speed fluid shunting, reduce the air flow velocity in the volute, simultaneously, lead the high-speed ram air to be diffused in the large-section volute, effectively improve the static pressure of the nozzle inlet, reduce the flow velocity, reduce the vortex and the friction loss, therefore, the refrigeration efficiency of the stamping turbine is improved, and the strict requirements on the performance and the space occupation of the refrigeration equipment under the airborne condition of the aircraft can be met.
In conclusion, the utility model discloses utilize the mode of structural topology optimization to empty the double volute runner that forms the nozzle both sides with the inside entity supporting structure of ram turbine under the condition that satisfies structural strength, increase spiral case runner sectional area under the prerequisite that does not increase the ram turbine volume, realize the purpose to high-speed ram air speed reduction diffusion, be favorable to the high-efficient work of ram turbine more, can also alleviate ram turbine weight simultaneously, reduce the aircraft load.
Drawings
FIG. 1 is a power turbine driven ram turbine cooling scheme;
FIG. 2 is a schematic structural diagram of the volute of the present invention;
fig. 3 is a schematic view of the airflow direction of the volute of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention.
As shown in fig. 2, 1 is a nozzle ring with a rectangular cross section of a power turbine, and is used for converting the total pressure of a fluid working medium into speed and providing sufficient driving torque for a power turbine 5; in the figure, 2, an inlet of a volute of the power turbine is connected with an air inlet channel and used for conveying fluid working media for a nozzle and the power turbine. FIG. 3 is a side annular constant cross-section volute flow path from the nozzle for uniform distribution of internal gas flow to the nozzle ring inlet; in the figure 4, the annular constant-section volute flow channel at the other side of the nozzle is shown; the high-flow-speed small-static-pressure fluid working medium conveyed through the volute inlet 2 enters a large-section flow channel formed by the volute flow channels on the two sides of the volute flow channel I3 and the volute flow channel II 4, and then the speed is fully reduced, the diffusion effect is achieved under the condition of approximate heat insulation, and therefore a small-flow-speed high-static-pressure area is formed at the nozzle inlet. In the figure, 5 is a power turbine, and in the figure 1, the power turbine is driven by high-speed airflow at the outlet of a nozzle to rotate at a high speed so as to output the working fluid to the outside, so that the specific enthalpy and the temperature of the fluid working medium are reduced, and the refrigeration function is realized. FIG. 6 shows a casing of the turbine engine to provide sealing and support for the internal flow passages and components.
4 are the original spiral case runner of power turbine in figure 2, adopt the fashioned mode of lathe work preparation to become the uniform cross section form, 3 in the figure for utilizing the inside supporting structure optimization fashioned spiral case runner of punching press turbine, also adopt the fashioned mode of lathe work preparation to become the uniform cross section form, the annular runner need not be the uniform cross section, traditional runner will be made the variable cross section in order to accord with the rule of the free vortex in plane, but the implementation degree of difficulty big cost height of variable cross section, the utility model discloses a behind the two side volutes, the runner sectional area increases, and air velocity is little, makes the more economized cost of uniform cross section, also easily realizes.
In the figure 2, a nozzle 1 with a rectangular cross section is manufactured by milling, the nozzle is arranged in the middle of volute flow channels on two sides, in the figure, a power turbine 5 is formed by milling, is supported and rotated by adopting a high-speed bearing and a rotating shaft, is arranged at the axle centers of a nozzle ring 1, a volute flow channel I3 and a volute flow channel II 4 in the figure 2, and is used for rotating an output shaft at a high speed under the pushing of high-speed airflow after the nozzle ring 1 is accelerated stably, so that enthalpy drop and temperature drop of working media are realized.
Specifically, the nozzle ring 1 and the volute flow channel 3 are integrally processed, the volute flow channel 3 is fastened with the housing 6 through screws 7, the volute flow channel 4 and the housing 6 are welded at a joint, and airflow flows out through the airflow outlet pipeline 8.
The utility model discloses the air current direction of spiral case is shown in figure 3, and is following right the utility model discloses a concrete principle carries out the analysis explanation:
the ram air total temperature at the inlet of the ram turbine refrigeration scheme of fig. 1 may be expressed as:
tt＝ts(1+Ma2/5)
the total pressure can be expressed as:
the local sound velocity is:
when the aircraft flies at 300 m high altitude at mach number 0.65, the total temperature of the ram air is 64 ℃, the total pressure is 129kPa, the local sonic velocity is 340m/s, and the airflow velocity corresponding to mach number 0.65 is 221m/s under the conditions that the ambient temperature is 38 ℃ and the atmospheric pressure is 99 kPa. It is known from fluid mechanics that the resistance loss is proportional to the square of the flow velocity, and a high-speed airflow with a speed per hour of 221m/s causes a great resistance loss when flowing in a flow passage before entering a nozzle, and the total pressure loss is as high as 10%, which has a great influence on the operation of a ram turbine with a low inlet total pressure, so that the part of ram air must undergo sufficient deceleration and diffusion before entering the nozzle and the turbine.
The relationship between the cross-sectional velocity and the flow rate of the gas flow can be expressed as:
q＝ρvA
when the design gas flow of the stamping turbine is 400kg/h, the air flow speed at the inlet of the square meter volute with the sectional area of 0.004 is 21m/s, the air flow speed at the inlet of the volute is 10.5m/s after the volute with double-side air inlet in the figure 2 is adopted, and the flow at the far end of the inlet of the volute is gradually reduced while the air flow continuously enters the nozzle along the volute, so that the air flow speed in the volute is further reduced to be close to a stagnation state.
By last, the utility model discloses an aviation punching press refrigeration turbine is with two side spiral casings that admit air with diffusion function lies in utilizing the inside bearing structure space of aviation punching press turbine to set up power turbine spiral casing runner, uses increase spiral casing runner sectional area with former spiral casing runner cooperation, plays the speed reduction diffusion effect to turbine entry aviation punching press air. Meanwhile, the weight of the stamping turbine can be reduced under the condition of unchanged volume. The bilateral air inlet volutes are both in an upper volute form and are positioned on two sides of the nozzle ring.
The utility model discloses an aviation punching press refrigeration turbine is with two side spiral casings that admit air with diffusion function for adopt aviation ram air to carry ring control cold turbine as power supply and refrigeration working medium's machine, the inside circulation sectional area of accessible increase spiral casing carries out speed reduction diffusion to the aviation ram air of atmosphere, high velocity of flow, little static pressure, reduces the loss of flow, promotes refrigeration efficiency. Meanwhile, the air flow velocity after diffusion is low and is close to a stagnation state, the requirement of axial symmetry exhaust of the variable cross section of the traditional volute is not required to be met, and the constant cross section volute form can be adopted, so that the difficulty in processing the volute is reduced. The bilateral volute that admits air is located inside the punching press refrigeration turbine, and the both sides of power turbine nozzle can effectively utilize the inside supporting structure space of turbine, need not to increase whole volume, can reduce organism weight simultaneously, and is more friendly to aviation machine carries the application.
The above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (8)
1. A bilateral air inlet volute for an aviation environment-controlled stamping refrigeration turbine comprises a shell (6), wherein a power turbine (5) is arranged in the shell (6), a nozzle ring (1) is correspondingly arranged on the power turbine (5), and the nozzle ring (1) is used for converting the total pressure of a fluid working medium into speed and providing driving torque for the power turbine (5);
the volute inlet (2) is arranged on the shell (6), and an annular flow channel is arranged in the shell (6);
an air outlet pipeline (8) is arranged on the shell (6), and air flows out through the air outlet pipeline (8);
the method is characterized in that:
the annular flow channel comprises a first volute flow channel (3) and a second volute flow channel (4), and the two volute flow channels are symmetrically arranged on two sides of the nozzle ring (1) respectively;
the volute inlet (2) is connected with the air inlet channel and used for conveying fluid working media, the fluid working media conveyed through the volute inlet (2) enter the large-section flow channel formed by the volute flow channels on the two sides of the volute flow channel I (3) and the volute flow channel II (4) and then can be decelerated, the diffusion effect is achieved, and therefore a small-flow-speed high-static-pressure area is formed at the inlet of the nozzle ring (1).
2. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the second volute flow channel (4) is the original volute flow channel of the power turbine (5), and the second volute flow channel (4) is manufactured into a uniform cross section form in a turning forming mode.
3. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 2, wherein: the volute flow channel I (3) is additionally arranged by utilizing an internal supporting structure of the stamping turbine, and the volute flow channel I (3) is manufactured into a uniform cross section form in a turning forming mode.
4. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the nozzle ring (1) is a rectangular-section nozzle manufactured by milling and is arranged in the middle of volute flow channels on two sides.
5. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the power turbine (5) is formed by milling, is supported by a high-speed bearing and a rotating shaft to rotate and is arranged at the axle center positions of the nozzle ring (1), the first volute flow channel (3) and the second volute flow channel (4).
6. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the nozzle ring (1) and the volute flow channel I (3) are integrally processed.
7. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the volute flow channel I (3) is fastened with the shell (6) through a screw (7).
8. The dual-sided inlet volute for an aviation environmentally controlled stamped refrigeration turbine of claim 1, wherein: the volute flow channel II (4) is connected with the shell (6) in a welding mode at a joint.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114033504A (en) * | 2021-11-05 | 2022-02-11 | 重庆江增船舶重工有限公司 | Liquid working medium spray cooling system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114033504A (en) * | 2021-11-05 | 2022-02-11 | 重庆江增船舶重工有限公司 | Liquid working medium spray cooling system |
| CN114033504B (en) * | 2021-11-05 | 2024-05-03 | 重庆江增船舶重工有限公司 | Liquid working medium spray cooling system |
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