Search

CN-121976959-A - Electric and gas hybrid driven high-efficiency aviation turbine and turbine cooling method

CN121976959ACN 121976959 ACN121976959 ACN 121976959ACN-121976959-A

Abstract

The invention discloses an electric and gas hybrid driven high-efficiency aviation turbine and a turbine cooling method, wherein the aviation turbine mainly comprises a turbine, a motor and a gas compressor, and specifically comprises a turbine shell, a turbine impeller, a gas guiding ring, a gas guiding end cover, a turbine check ring, a bearing, a motor, a shaft sleeve, a gas guiding shell, a sealing end cover, a diffuser, a gas compressor impeller, a gas compressor shell, a gas compressor check ring and a protective filter screen. The motor is of a double-output shaft type, the turbine and the air compressor are respectively arranged on two sides of the motor shaft, the motor is driven by an air dynamic bearing, the shell of the motor is provided with air holes, and external air is led to respectively dissipate heat of the motor and the bearing. When the aircraft works at high altitude, the motor does not participate in output, and when the aircraft works at low altitude, the motor is put into operation and used as a second section of power source of the turbine cooler to perform compensation work for the turbine cooler, and the heat dissipation efficiency of the turbine cooler is improved through the output work of the motor. The invention meets the technical requirements of small volume, high efficiency, low power consumption and adjustable gear.

Inventors

  • ZHANG YUANQIAN
  • PAN SHAOPING
  • LI CHUANCAI
  • LI JIANGZHOU

Assignees

  • 贵州永红航空机械有限责任公司

Dates

Publication Date
20260505
Application Date
20260121

Claims (10)

  1. 1. The high-efficiency aviation turbine driven by electric and gas mixing is characterized by comprising a turbine shell (1), a turbine impeller (2), a gas-entraining ring (3), a flow guide end cover (4), a turbine end cover (5), a turbine retainer ring (6), a bearing (7), a motor, a shaft sleeve (9), a gas-entraining shell (11), a sealing end cover (12), a diffuser (13), a gas compressor impeller (14), a gas compressor shell (15), a gas compressor retainer ring (16) and a protective filter screen (17), wherein: The air entraining shell (11) is positioned between the turbine shell (1) and the air compressor shell (15), the turbine shell (1), the air entraining shell (11) and the air compressor shell (15) are connected together to form the appearance of the aviation turbine, The air entraining shell (11) is provided with an air entraining hole and a socket; The motor comprises a motor shell (10) and a motor shaft (8), wherein the motor shell (10) is positioned in an air entraining shell (11) and is arranged between a turbine shell (1) and a gas compressor shell (15), a closed cavity is formed between the motor shell (10) and the air entraining shell (11), heat dissipation partition plates are uniformly distributed on the surface of the motor shell (10), holes are formed in the motor shell (10), and the motor shaft (8) is positioned in the motor shell (10) and extends to the turbine shell (1) and the gas compressor shell (15) respectively after penetrating through the two axial ends of the motor shell (10) so as to be connected with a turbine impeller (2) and a gas compressor impeller (14); the turbine impeller (2) is assembled in the turbine shell (1), and the turbine impeller (2) is provided with a gas-introducing hole; the flow guide end cover (4) is arranged on an axial end cover of the motor shell (10), the flow guide end cover (4) is positioned at the outer edge of the turbine impeller (2), and static guide vanes are uniformly distributed on the surface of the flow guide end cover (4); The turbine end cover (5) is positioned between the motor shell (10) and the turbine impeller (2), and the surface of the turbine end cover (5) is provided with a multi-stage labyrinth seal structure and is matched with the end face of the turbine impeller (2) to form dynamic seal; The two air entraining rings (3) are respectively positioned at the tail ends of the turbine impeller (2) and the compressor impeller (14) and are assembled on the motor shaft (8), and spiral grooves are formed in the surface of the air entraining rings (3) along the circumferential direction; the turbine check ring (6) is positioned between the turbine impeller (2) and the axial end face of the motor shell (10), the turbine check ring (6) is formed by splicing a plurality of layers of plates with different apertures, and an inner hole of the turbine check ring (6) is assembled with the outer surface of the air entraining ring (3); The shaft sleeve (9) is positioned in the motor shell (10), the bearing (7) is arranged on the shaft sleeve (9), the inner ring of the bearing (7) is assembled with the motor shaft (8), and a plurality of air holes are formed in the shaft sleeve (9); the sealing end cover (12) is positioned between the compressor impeller (14) and the motor shell (10), and the sealing end cover (12) is provided with a sealing structure in the axial direction and the radial direction and forms dynamic seal with the compressor impeller (15); The compressor impeller (14) is assembled in the compressor shell (15), and the compressor impeller (14) is provided with an air introducing hole; the diffuser (13) is positioned at the outer edge of the compressor impeller (14), and the diffuser (13) and the compressor shell (15) form a pressure air cavity; the air compressor check ring (16) is positioned at the front end of the air compressor impeller (14) and the inlet end of the air compressor, the air compressor check ring (16) is formed by splicing a plurality of layers of baffles with different apertures, and the air compressor check ring is attached to the air compressor impeller (14) to effectively prevent redundant matters from the front end from entering the air introducing hole of the air compressor impeller (14).
  2. 2. The high-efficiency aviation turbine driven by electricity and gas mixture as claimed in claim 1, wherein the section of the turbine shell (1) is radial air inlet and axial air outlet, and a casing line formed by inner contour lines of the turbine shell (1) is changed along with the profile of blade tips of blades of the turbine impeller (2) from an air inlet to an air outlet of the turbine shell (1) and has consistent change trend.
  3. 3. The high-efficiency aviation turbine driven by mixed electricity and gas according to claim 1, wherein a casing line formed by inner contour lines of the compressor housing (15) changes along with blade tip molded lines of the compressor impeller (14) from an air inlet of the compressor housing (15) to the side of the compressor housing (15) and has consistent change trend.
  4. 4. An electric, gas hybrid drive high efficiency aero turbine as claimed in claim 1 wherein said turbine wheel (2) blades are all diagonal flow airfoil blades having progressively decreasing radial height from the air inlet side to the air outlet side blades.
  5. 5. The high-efficiency aero turbine driven by mixed electricity and gas according to claim 1, wherein the blades of the compressor impeller (14) are all oblique flow type wing blades and are of a closed structure, and the radial height of the blades gradually decreases from the air inlet side to the air outlet side.
  6. 6. An electric, gas hybrid drive high efficiency aero turbine according to claim 1, characterised in that the surface of the motor shaft (8) is provided with grooves for the bleed air to dissipate heat from the rotor inside the motor housing (10).
  7. 7. An electric and gas hybrid driven high efficiency aviation turbine according to claim 1, characterized in that the turbine housing (1) and the gas inlet of the compressor housing (15) are both provided with a protective screen (17).
  8. 8. The high-efficiency aviation turbine driven by electric and gas mixture as claimed in claim 1, wherein the rotation speed of the aviation turbine is 6000r/min or less, the turbine end flow is 85 kg/h-100 kg/h, the expansion ratio is 18.2 or less, and the compressor end pressure ratio is 2.1.
  9. 9. An electric, gas hybrid driven high efficiency aero turbine as claimed in claim 1, wherein: The turbine shell (1), the air entraining shell (11), the motor shell (10) and the air compressor shell (15) are connected through screws or integrally formed; the turbine impeller (2) and the compressor impeller (14) are arranged on the motor shaft (8) through self-locking nuts.
  10. 10. A turbine cooling method suitable for an aircraft environmental control system is characterized in that the high-efficiency aviation turbine driven by electric and gas mixture is adopted and comprises the following steps: When the aircraft works at high altitude, the motor does not work, high-temperature high-pressure air flows are guided by the guide end cover (4) to apply work to the turbine impeller (2) after entering the turbine shell (1) in the radial direction, low-temperature low-pressure air flows are axially discharged, the output mechanical work drives the compressor impeller (14) to rotate at high speed through the motor shaft (8), so that the pressure of air flowing through the compressor shell (15) is increased, high-pressure air is obtained, and the air enters the compressor shell (15) from the diffuser (13) in the axial direction and is radially discharged to dissipate heat of the equipment cabin after being pressurized; When the aircraft works at low altitude, the motor is put into operation to serve as a second section of power source of the aviation turbine, and compensation work is performed for the aviation turbine.

Description

Electric and gas hybrid driven high-efficiency aviation turbine and turbine cooling method Technical Field The invention belongs to the technical field of ventilation, pressurization source equipment and turbine coolers of aircraft fuel systems, and is particularly suitable for turbine coolers with different working conditions and heat dissipation requirements, in particular to an electric and gas hybrid-driven high-efficiency aviation turbine which is suitable for cooling circulation in the fields of aerospace, ships, electronics and the like. Background The turbine cooler is an important refrigeration technology in the fuel oil cooling system of the current civil aircraft and fighter aircraft environmental control system, and has the function of converting high-temperature high-pressure air at the air inlet end of the turbine into low-temperature low-speed air through the turbine cooler to cool and dissipate heat of the cabin and other equipment cabins on the aircraft. With the development of electronic equipment and the improvement of integration level, the requirements on the refrigeration and pressurization technology of the turbine cooler are also higher and higher. In the traditional refrigeration mode, the turbine cooler is only of a single wheel type, the structural function is single, the turbine refrigeration air outlet and the compressor boosting air outlet are the same air flow, and the defects such as poor refrigeration effect, large turbine power consumption, large accompanying volume, unbalanced axial force and the like exist. In order to cope with the increasingly severe environmental demands, various refrigeration modes such as TC, TTCC, TTC, TTCF and other technologies are sequentially generated, and the refrigeration efficiency and stability are improved by changing the flow direction of air flow and adding some intermediate processes. However, with the continuous improvement of the integration level of electronic equipment, the heat flux density and the heat dissipation power of the equipment are larger and larger, the load of the electronic heat dissipation equipment is further increased, and higher requirements are put on the performance and the stability of the turbine refrigerator. The refrigerating efficiency and the power consumption installation volume of the turbine cooler are all the time difficult problems in the domestic aviation field, particularly, the gas pressure at the air inlet end of the turbine in low-altitude flight is low, the refrigerating efficiency is low, and in order to solve the problems, it is necessary to design an electric and gas hybrid-driven high-efficiency aviation turbine, and meanwhile, the problems of service life, heat dissipation, sealing and stability caused by the fact that a motor is introduced into the turbine cooler are solved. Disclosure of Invention The invention aims to provide an electric and gas hybrid driven high-efficiency aviation turbine and a turbine cooling method, and provides a turbine cooler suitable for an aircraft environmental control system according to specified technical indexes such as air quantity, air pressure, heat dissipation power consumption, structural size and the like, so that the technical requirements of small volume, high efficiency, low power consumption and adjustable gear are met, and the problems of service life, heat dissipation, sealing and stability of a motor are solved. In order to achieve the above purpose, the present invention adopts the following technical scheme: the utility model provides an electricity, gas hybrid drive's high efficiency aviation turbine, includes turbine casing, turbine wheel, draws gas ring, water conservancy diversion end cover, turbine retaining ring, bearing, motor, axle sleeve, air entraining casing, seal end cover, diffuser, compressor impeller, compressor casing, compressor retaining ring and protection filter screen, wherein: the bleed air shell is positioned between the turbine shell and the compressor shell, and the turbine shell, the bleed air shell and the compressor shell are connected together to form the appearance of the aviation turbine, The air entraining shell is provided with an air entraining hole and a socket; the motor comprises a motor shell and a motor shaft, wherein the motor shell is positioned in the air entraining shell and is arranged between the turbine shell and the air compressor shell, a closed cavity is formed between the motor shell and the air entraining shell, and heat dissipation partition plates are uniformly distributed on the surface of the motor shell and are provided with holes; The turbine impeller is assembled in the turbine shell, and the turbine impeller is provided with an air introducing hole; The flow guide end cover is arranged on the axial end cover of the motor shell, the flow guide end cover is positioned at the outer edge of the turbine impeller, and static guide vanes are uniformly distributed on the surface of the flow g