T-C-F type three-wheel aviation turbine cooler

Abstract

The invention discloses a T-C-F type three-wheel aviation turbine cooler. An axial force balance area, a sealing boss and a thrust boss are sequentially arranged on the back of the turbine in the axial direction, the thrust boss is connected with a thrust plate, the thrust plate is connected with the back of an impeller of a gas compressor through a short shaft, and the inlet end of the impeller of the gas compressor is connected with a fan through a long shaft. The turbine near end of the thrust plate is sleeved with a thrust flange, a floating sealing groove A and a floating sealing groove B are sequentially formed in the thrust flange in the axial direction towards an air outlet of the turbine, the floating sealing groove A and the turbine near end of the thrust plate are in dynamic sealing in the radial direction through a floating sealing assembly A, and the floating sealing groove B and the sealing boss are in dynamic sealing in the radial direction through a floating sealing assembly B; the periphery of the short shaft is rotationally connected with a connecting section between the turbine volute and the gas compressor volute through a radial bearing A. The far end of a turbine of the short shaft extends out of the connecting section and then is dynamically sealed through a floating sealing assembly C. The problems that an existing three-wheel turbine is poor in compactness, low in outlet anti-icing efficiency, low in impeller pneumatic efficiency and poor in fan volute strength are solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft environmental control system, and particularly relates to a T-C-F type three-wheel aviation turbine cooler. BACKGROUND

[0002] The airborne three-wheel turbine cooler is a core component of the aircraft environmental control system, in order to improve product reliability and prolong product service life, a large number of turbine coolers adopt air bearing support, and the traditional internal structure has the following disadvantages: 1. The shaft neck seal adopts a traditional mechanical seal, and the parallelism, perpendicularity and shaft runout error of the sealing surface need to be strictly ensured during installation, otherwise early failure is easy to occur, the single-stage sealing leakage rate is high, the misalignment (0.1-0.3mm) of the shaft is poor in adaptability, and the vibration or eccentricity of the high-speed rotating shaft can cause the gap between the sealing surfaces to change, causing leakage or uneven contact, aggravating wear, and it is difficult to meet the long life (>10000 hours) requirement of the aviation equipment.

[0003] 2. The air bearing cooling effect is not ideal, and the radial and thrust air bearings are easy to burn out under the condition of high-speed operation and extreme onboard working conditions; 3. The bearing cooling air supply filtering device adopts a common filter element mode, and the inside is blocked after a certain period of use, and needs to be replaced regularly; 4. The back seal gap cannot be too large, the swing track of the rotor supported by the radial air bearing needs to be considered, the axial force balance effect is poor, and the thrust bearing is easy to overload and damage; 5. The inlet and outlet of the fan flow passage exist 180° reverse folding, the efficiency matching of the fan and the shell is poor, and aerodynamic loss is caused; 6. The deicing heating sleeve has poor heating effect on the gas at the turbine outlet, the heating rate is slow, and the ice at the outlet causes damage to the inner wall of the turbine impeller and volute. SUMMARY

[0004] The present application aims to provide a T-C-F type three-wheel aviation turbine cooler. The present application solves the problems of poor compactness of the existing three-wheel turbine structure, regular replacement of the filter, low outlet anti-icing efficiency, low impeller aerodynamic efficiency and poor fan volute strength.

[0005] Technical Solution. A TCF-type three-wheeled aircraft turbine cooler, comprising a turbine volute, a compressor volute, and a fan volute arranged sequentially along the axial direction. A turbine, a compressor impeller, and a fan are correspondingly housed within each of the turbine volute, compressor volute, and fan volute. An axial force balance zone, a sealing boss, and a thrust boss are sequentially provided along the back of the turbine. The thrust boss is connected to a thrust plate, which is connected to the back of the compressor impeller via a short shaft. The inlet end of the compressor impeller is connected to the fan via a long shaft. A thrust flange is fitted near the turbine end of the thrust plate. Floating sealing grooves A and B are sequentially provided along the axial direction of the thrust flange towards the turbine outlet. Floating sealing groove A... The turbine near the thrust disc is dynamically sealed radially by floating seal assembly A, and the floating seal groove B and the sealing boss are dynamically sealed radially by floating seal assembly B. The periphery of the short shaft is rotatably connected to the connecting section between the turbine volute and the compressor volute via radial bearing A, and the turbine far end of the short shaft extends out of the connecting section and is dynamically sealed by floating seal assembly C. The periphery of the long shaft is rotatably connected to the fan volute via radial bearing B, and the two ends of radial bearing B are dynamically sealed by floating seal assembly D and floating seal assembly E, respectively. The cavity where floating seal assembly C is located is connected to the outlet end of the compressor volute, and the axial force balance zone is connected to the inlet end of the turbine volute.

[0006] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, a baffle plate is installed in the axial force balance zone, and a guide flange is provided on the outer edge of the baffle plate facing the turbine side.

[0007] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, the thrust disc is rotatably connected to the thrust flange via a forward thrust bearing, and the thrust disc is rotatably connected to the turbine volute via a reverse thrust bearing.

[0008] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, the cavity where the thrust disc is located is connected to the turbine volute inlet end via an air filter.

[0009] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, adjusting shims are placed between the forward thrust bearing and the thrust flange and / or between the reverse thrust bearing and the turbine volute.

[0010] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, a heating jacket is provided between the turbine volute and the turbine, and a spiral flow channel is provided between the heating jacket and the turbine volute. The inlet of the spiral flow channel is connected to the air outlet of the compressor volute, and the outlet of the spiral flow channel is connected to the air inlet of the compressor volute.

[0011] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, a protective ring is provided in the jacketed cavity of the turbine volute surrounding the fan.

[0012] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, the air filter includes an induction pipe, which has a spiral structure, an impurity collection jacket cavity, and a purification outlet arranged axially in sequence inside the induction pipe. The impurity collection jacket cavity is connected to the external environment through an impurity discharge hole; the purification outlet is connected to the cavity where the thrust plate is located.

[0013] In the aforementioned TCF-type three-wheeled aircraft turbine cooler, the cavity where the thrust disc is located is connected to the cavity where the radial bearing A is located. The radial bearing A is connected to the inner cylinder of the short shaft through the radial hole of the short shaft. The inner cylinder of the short shaft is connected to the inner cylinder of the long shaft. The inner cylinder of the long shaft is connected to the cavity where the radial bearing B is located through the radial hole of the long shaft.

[0014] The beneficial effects of the present invention are as follows: The present invention designs an axial force balance zone on the back of the turbine, which is connected to the inlet end of the turbine volute and connects the cavity where the floating seal component C is located to the outlet end of the compressor volute; this structure can provide a pair of axial forces in opposite directions in the axial force balance zone and the cavity where the floating seal component C is located, which can greatly solve the axial force problem.

[0015] The five-point floating seal structure designed in this invention can better compensate for the misalignment of the shaft caused by eccentricity, thermal expansion, or vibration. The floating seals between each level can also effectively prevent gas particles from entering the air bearing, achieving the goal of long-term bearing operation. The baffle plate can effectively prevent the formation of vortexes that cause corrosion when gas suddenly enters the product, while also achieving the purpose of gas diversion and extending the service life of components; The thrust bearing employs a dual-clearance adjustment method. One method involves adjusting the axial clearance by adding or removing shims on the thrust bearing housing. The other method utilizes two types of mating shims designed into the thrust bearing itself to adjust the axial clearance, and these shims also increase the bearing's load-bearing stiffness. When the bearing's own stiffness is insufficient to withstand greater loads, shims are used to reinforce its load-bearing capacity, while the clearance adjustment uses a different method. This structure increases the adjustability of the axial clearance and ensures the thrust bearing's load-bearing stiffness. It effectively solves the problem of insufficient stiffness caused by inadequate thrust bearing clearance adjustment when adjusting the clearance unilaterally, and makes axial movement easier to adjust.

[0016] The fan impeller is equipped with a protective device to prevent the fan impeller or foreign objects from breaking the casing and causing injury to the operator, which can reduce weight and provide protection.

[0017] In summary, the TCF-type three-wheel turbine cooler of the present invention has structural features such as journal floating seal, spiral air filter, spiral heating jacket, new type of baffle plate, guide vane type reinforcing rib, integrated axial force balance and bearing cooling, which solves the problems of poor compactness of existing three-wheel turbine structures, need for regular filter replacement, low outlet anti-icing efficiency, low impeller aerodynamic efficiency and poor fan volute strength. Attached Figure Description

[0018] Figure 1 This is the internal overall structure of the TCF three-wheel turbine cooler of the present invention; Figure 2 This is the external integral structure of the TCF three-wheel turbine cooler of the present invention; Figure 3 This is a schematic diagram of the internal gas flow and cooling process; Figure 4 This is a schematic diagram of an axial force balance structure. Figure 5 This is a schematic diagram of the novel baffle plate structure; Figure 6 This is a schematic diagram of a spiral dual-channel filter structure; Figure 7 Schematic diagram of the turbine outlet spiral heating jacket; Figure 8 Schematic diagram of fan volute protection and guide vane reinforcing rib device; Figure 9 shows a schematic diagram of the installation structure of radial and thrust air bearings, where (a) is the installation of thrust air bearings; and (b) is the installation of radial air bearings. Figure 10 Diagram of stop-pull order; Figure 11 Schematic diagram of push flange. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0021] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] Example 1. A TCF-type three-wheeled aircraft turbine cooler, see [link / reference]. Figures 1-11 The turbine volute 1, compressor volute 2, and fan volute 3 are arranged sequentially along the axial direction. A turbine 4, compressor impeller 5, and fan 6 are correspondingly housed within each of these three volutes. The back of the turbine 4 is provided with an axial force balance zone 7, a sealing boss 8, and a thrust boss 9 arranged sequentially along the axial direction. The thrust boss 9 is connected to a thrust plate 10. The thrust plate 10 is connected to the back of the compressor impeller 5 via a short shaft 11. The inlet end of the compressor impeller 5 is connected to the fan 6 via a long shaft 12. A thrust flange 13 is fitted onto the turbine proximal end of the thrust plate 10. The thrust flange 13 has floating sealing grooves A14 and B15 arranged sequentially along the axial direction towards the turbine outlet. The floating sealing groove A14 is connected to the thrust plate 10... The turbine near end is dynamically sealed radially by floating seal assembly A16, and the floating seal groove B15 and the sealing boss 8 are dynamically sealed radially by floating seal assembly B17. The periphery of the short shaft 11 is rotatably connected to the connecting section between the turbine volute 1 and the compressor volute 2 via radial bearing A18. The turbine far end of the short shaft 11 extends out of the connecting section and is dynamically sealed by floating seal assembly C19. The periphery of the long shaft 12 is rotatably connected to the fan volute 3 via radial bearing B20. The two ends of the radial bearing B20 are dynamically sealed by floating seal assembly D21 and floating seal assembly E22, respectively. The cavity where the floating seal assembly C19 is located is connected to the outlet end of the compressor volute 2, and the axial force balance zone 7 is connected to the inlet end of the turbine volute 1.

[0023] High-temperature, high-pressure air from the engine is cooled by the primary radiator before entering the inlet of the ACM compressor volute 2. Due to centrifugal force during high-speed rotation, the gas pressure and temperature increase. It then passes through the blade diffuser and compressor volute, further increasing its pressure and temperature. The high-temperature, high-pressure gas exiting the compressor volute 2 outlet is cooled by the secondary radiator before entering the turbine volute 1 inlet. The high-pressure, low-temperature air enters the turbine rectifier window through the turbine volute 1 inlet, where it expands and accelerates, converting some of the airflow's thermal energy into kinetic energy. The high-speed airflow impacts the turbine blades, causing the turbine to rotate. The kinetic energy of the airflow is then converted into mechanical work, driving the centrifugal compressor. The airflow temperature decreases, and it is discharged from the heating jacket connected to the turbine volute 1 outlet, passing through a low-pressure water separator into the cabin for cooling and temperature regulation. Simultaneously, the rotor drives the fan to rotate, converting atmospheric air into axial airflow.

[0024] Because the product uses air bearings, the rotor system will have a certain degree of eccentricity when rotating. The five seals together form a multi-stage floating seal structure, which can better compensate for the eccentricity of the shaft, the offset caused by thermal expansion or vibration. The floating seals between each stage can also effectively prevent gas particles from entering the air bearing, so as to achieve the purpose of long-term bearing operation.

[0025] A baffle plate 23 is installed in the aforementioned axial force balance zone 7, and a guide flange 24 is provided on the outer edge of the baffle plate 23 facing the turbine side. This structure is used to prevent the formation of a cyclone at the thrust flange 13 when gas flows in, which would erode the thrust flange 13 and the turbine housing and affect its service life.

[0026] The aforementioned thrust disc 10 is rotatably connected to the thrust flange 13 via a forward thrust bearing 25, and the thrust disc 10 is rotatably connected to the turbine housing 1 via a reverse thrust bearing 26.

[0027] The cavity where the aforementioned thrust plate 10 is located is connected to the air intake end of the turbine housing 1 via the air filter 27.

[0028] Adjusting shims are placed between the aforementioned forward thrust bearing 25 and the thrust flange 13 and / or between the reverse thrust bearing 26 and the turbine housing 1. Because the thrust bearings are installed in one cavity, when the thrust disc 10 rotates, it will form an air film with a thickness on the order of micrometers between itself and the forward thrust bearing 25 and the reverse thrust bearing 26. If the gap between the thrust disc 10 and the forward thrust bearing 25 and the reverse thrust bearing 26 is too large or too small, it will be difficult to form an air film. The purpose of the adjusting shims is to adjust the gap between the thrust disc 10 and the forward thrust bearing 25 and the reverse thrust bearing 26. The thrust bearing is equipped with a dual clearance adjustment structure during installation. One clearance adjustment involves adding or removing shims on the thrust bearing housing to adjust the axial clearance. The other clearance adjustment involves designing two types of matching shims on the thrust bearing itself to adjust the axial clearance, and these shims can also increase the bearing's load-bearing stiffness. When the bearing's own stiffness is insufficient to withstand greater stiffness, the bearing's own shims are used to strengthen its load-bearing capacity. The clearance adjustment is performed using a different method. This structure increases the adjustability of the axial clearance and ensures the load-bearing stiffness of the thrust bearing.

[0029] A heating jacket 28 is provided between the aforementioned turbine volute 1 and turbine 4. A spiral flow channel 29 is provided between the heating jacket 28 and turbine volute 1. The inlet of the spiral flow channel 29 is connected to the outlet end of the compressor volute 2, and the outlet of the spiral flow channel 29 is connected to the inlet end of the compressor volute 2. After the compressor impeller 5 and compressor volute 2 perform mechanical work, they will form high-temperature and high-pressure gas. After the turbine 4 and turbine volute 1 perform mechanical work, they will form low-temperature gas. To prevent icing at the tip of the turbine 4 blades, high-temperature and high-pressure gas is drawn from the outlet of the compressor volute 2 through an external pipe to heat the heating jacket to prevent icing at the tip of the turbine 4 blades. After rotating once outside the heating jacket 28, the heated gas returns to the inlet of the compressor volute 2 through another external pipe.

[0030] The aforementioned fan 6 has a protective ring 30 installed in the interlayer cavity of the turbine casing 1. This achieves both weight reduction and prevents injury to the operator from fan impeller malfunctions.

[0031] The aforementioned air filter 27 includes an induction pipe 31, within which a spiral structure 32, an impurity collection interlayer cavity 33, and a purification outlet 34 are sequentially arranged axially. The impurity collection interlayer cavity 33 is connected to the external environment via an impurity discharge hole 35; the purification outlet 34 is connected to the cavity where the thrust plate 10 is located. The filter has a dual-channel internal structure. Impurities reach the impurity collection interlayer cavity 33 through the spiral centrifugal force, and are discharged under the influence of gas flow. The filtered gas flows directly through the purification outlet 34 to the foil bearing to cool the bearing.

[0032] The cavity containing the aforementioned thrust disc 10 is connected to the cavity containing the radial bearing A18. The radial bearing A18 is connected to the inner cylinder of the short shaft 11 via the short shaft radial hole 36. The inner cylinder of the short shaft 11 is connected to the inner cylinder of the long shaft 12. The inner cylinder of the long shaft 12 is connected to the cavity containing the radial bearing B20 via the long shaft radial hole 37. Cooling air is introduced into the thrust bearing chamber through the filter 27. Part of the cooling air flows in along the forward thrust bearing 25, and part flows in along the reverse thrust bearing 26. The air flowing down from the forward thrust bearing 25 enters the chamber through the annular seal, and then is delivered to the turbine outlet through the turbine head. This small air leakage can also de-ice the turbine impeller. The air from the reverse thrust bearing 26 cools the radial bearing along the radial bearing sleeve, then enters the rotor through the hole on the short shaft 11, reaches the fan-side radial bearing through the hole on the long shaft 12 for cooling, and is discharged into the fan outlet.

[0033] In summary, this invention discloses an internal structure of a TCF-type three-wheeled aircraft turbine cooler, mainly including a compressor boosting unit, a turbine cooling unit, a fan unit, an air foil bearing support and cooling unit, a floating seal and axial force balancing unit, an bleed air filter unit, and a turbine volute anti-icing heating unit. External air first enters the compressor impeller, diffuser, and compressor housing sequentially for pressurization, then enters the interstage radiator for cooling, and subsequently enters the volute, rectifier window, and turbine sequentially, expanding and cooling before exiting. The coaxially rotating fan impeller is used to draw in external air, serving as the cold side of the interstage radiator. First, to prevent turbine outlet icing, a stream of high-temperature, high-pressure gas is drawn from the compressor outlet to the turbine-end spiral heating jacket, and then returns to the compressor inlet via the turbine volute. Second, to cool the air bearings, a stream of gas is drawn from the turbine inlet through a spiral dual-channel filter to remove impurities such as water, oil, and dust before flowing to the thrust bearing and adjacent radial bearings for heat dissipation. Third, considering axial force balance and impeller efficiency improvement, a novel floating seal structure is adopted to prevent the shaft system from jamming due to insufficient sealing ring clearance during high-speed rotation. Finally, guide vane-shaped reinforcing ribs are arranged at the fan housing inlet to increase strength and improve fan aerodynamic efficiency. This invention has the advantages of good turbine-end icing prevention, no need for periodic filter element replacement for bearing cooling, good dynamic sealing effect, high fan efficiency, and compact, high-strength, and low-weight overall structure.

[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.

Claims

1. A TCF-type three-wheeled aircraft turbine cooler, characterized in that, A turbine volute (1), a compressor volute (2), and a fan volute (3) are arranged sequentially along the axial direction. A turbine (4), a compressor impeller (5), and a fan (6) are respectively provided inside the turbine volute (1), compressor volute (2), and fan volute (3). An axial force balance zone (7), a sealing boss (8), and a thrust boss (9) are arranged sequentially along the axial direction on the back of the turbine (4). The thrust boss (9) is connected to the thrust plate (10). The thrust plate (10) is connected to the back of the compressor impeller (5) via a short shaft (11). The inlet end of the compressor impeller (5) is connected to the fan (6) via a long shaft (12). A thrust flange (13) is fitted on the turbine proximal end of the thrust plate (10). A floating sealing groove A (14) and a floating sealing groove B (15) are arranged sequentially along the axial direction towards the turbine outlet on the thrust flange (13). The floating sealing groove A (14) and the thrust flange (15) are connected to the turbine impeller (5) via a short shaft (11). The turbine proximal end of the thrust disc (10) is dynamically sealed radially by floating seal assembly A (16), and the floating seal groove B (15) and the sealing boss (8) are dynamically sealed radially by floating seal assembly B (17). The periphery of the short shaft (11) is rotatably connected to the connecting section between the turbine volute (1) and the compressor volute (2) via radial bearing A (18). The turbine distal end of the short shaft (11) extends out of the connecting section and is dynamically sealed by floating seal assembly C (19). The periphery of the long shaft (12) is rotatably connected to the fan volute (3) via radial bearing B (20). The two ends of the radial bearing B (20) are dynamically sealed by floating seal assembly D (21) and floating seal assembly E (22) respectively. The cavity where the floating seal assembly C (19) is located is connected to the outlet end of the compressor volute (2), and the axial force balance zone (7) is connected to the inlet end of the turbine volute (1).

2. The TCF-type three-wheeled aircraft turbine cooler according to claim 1, characterized in that, A baffle plate (23) is installed in the axial force balance zone (7), and a guide flange (24) is provided on the outer edge of the baffle plate (23) facing the turbine side.

3. The TCF-type three-wheeled aircraft turbine cooler according to claim 1, characterized in that, The body of the thrust disc (10) is rotatably connected to the thrust flange (13) via a forward thrust bearing (25), and the body of the thrust disc (10) is rotatably connected to the turbine volute (1) via a reverse thrust bearing (26).

4. The TCF-type three-wheeled aircraft turbine cooler according to claim 3, characterized in that, The cavity where the thrust disc (10) is located is connected to the air intake end of the turbine volute (1) via the air filter (27).

5. The TCF-type three-wheeled aircraft turbine cooler according to claim 3, characterized in that, Adjusting shims are placed between the forward thrust bearing (25) and the thrust flange (13) and / or between the reverse thrust bearing (26) and the turbine housing (1).

6. The TCF-type three-wheeled aircraft turbine cooler according to claim 1, characterized in that, A heating jacket (28) is provided between the turbine volute (1) and the turbine (4). A spiral flow channel (29) is provided between the heating jacket (28) and the turbine volute (1). The inlet of the spiral flow channel (29) is connected to the outlet of the compressor volute (2), and the outlet of the spiral flow channel (29) is connected to the inlet of the compressor volute (2).

7. The TCF-type three-wheeled aircraft turbine cooler according to claim 1, characterized in that, A protective ring (30) is provided in the interlayer cavity of the turbine volute (1) surrounding the fan (6).

8. The TCF-type three-wheeled aircraft turbine cooler according to claim 7, characterized in that, The air filter (27) includes an induction pipe (31), and the induction pipe (31) is provided with a spiral structure (32), an impurity collection interlayer cavity (33) and a purification outlet (34) in sequence along the axis. The impurity collection interlayer cavity (33) is connected to the external environment through the impurity discharge hole (35); the purification outlet (34) is connected to the cavity where the thrust plate (10) is located.

9. The TCF-type three-wheeled aircraft turbine cooler according to claim 8, characterized in that, The cavity where the thrust plate (10) is located is connected to the cavity where the radial bearing A (18) is located. The radial bearing A (18) is connected to the inner cylinder of the short shaft (11) through the radial hole (36) of the short shaft. The inner cylinder of the short shaft (11) is connected to the inner cylinder of the long shaft (12). The inner cylinder of the long shaft (12) is connected to the cavity where the radial bearing B (20) is located through the radial hole (37) of the long shaft.

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