Aero-engine turbine assembly

Patent metadata

Field	Value
Publication number	US-12012864-B2
Application number	US-202217973746-A
Country	US
Kind code	B2
Filing date	Oct 26, 2022
Priority date	Mar 29, 2022
Publication date	Jun 18, 2024
Grant date	Jun 18, 2024

Abstract

Disclosed is an aero-engine turbine assembly, including a turbine assembly body and a cooling component. The turbine assembly body is provided with an internal flow passage, and the turbine assembly body includes a turbine rotor disk, a blade end wall and a turbine rotor blade, which are successively fixedly connected with each other. The internal flow passage passes through the turbine rotor disk, the blade end wall and the turbine motor blade, and the internal flow passage is provided with an inlet and an outlet. The cooling component is fixed on the turbine rotor disk, and the cooling component includes an electromagnetic pump system, an expansion joint and a radiator, which are successively communicated with each other. The electromagnetic pump system is communicated with the inlet, to inject liquid metal to into the internal flow passage.

First claim

What is claimed is:

1. An aero-engine turbine assembly, comprising:
a turbine assembly body with an internal flow passage, wherein the turbine assembly body comprises a turbine rotor disk, a blade end wall and a turbine rotor blade, which are successively fixedly connected with each other; the internal flow passage passes through the turbine rotor disk, the blade end wall and the turbine rotor blade; and the internal flow passage is provided with an inlet and an outlet; and
a cooling component fixedly connected on the turbine rotor disk, wherein the cooling component comprises an electromagnetic pump system, an expansion joint and a radiator, which are successively in communication with each other; the electromagnetic pump system is in communication with the inlet to inject liquid metal into the internal flow passage; the radiator is in communication with the outlet to receive the liquid metal flowing out of the outlet.

2. The aero-engine turbine assembly according to claim 1 , wherein the inlet and the outlet are located on the turbine rotor disk.

3. The aero-engine turbine assembly according to claim 2 , wherein the aero-engine turbine assembly further comprises a drag reduction cover plate configured for reducing wind resistance; the drag reduction cover plate is fixed on the turbine rotor disk and covers an outside of the electromagnetic pump system and the expansion joint; and a side of the drag reduction cover plate away from the turbine rotor disk has a smooth surface.

4. The aero-engine turbine assembly according to claim 2 , wherein the electromagnetic pump system is in communication with the inlet via a first connecting pipe, the radiator is in communication with the outlet via a second connecting pipe, the radiator is in communication with the expansion joint via a third connecting pipe, and the expansion joint is in communication with the electromagnetic pump system via a fourth connecting pipe.

5. The aero-engine turbine assembly according to claim 1 , wherein the internal flow passage comprises a first bottom chamber, a second bottom chamber, a top chamber, a plurality of inflow blade cooling channels, and a plurality of outflow blade cooling channels, which are arranged in the turbine rotor blade; the first bottom chamber and the second bottom chamber are arranged at a side of the turbine rotor blade close to the blade end wall, and the top chamber is arranged at a side of the turbine rotor blade away from the blade end wall; the first bottom chamber is in communication with the top chamber via the plurality of inflow blade cooling channels, and the second bottom chamber is in communication with the top chamber via the plurality of outflow blade cooling channels.

6. The aero-engine turbine assembly according to claim 5 , wherein the internal flow passage further comprises a blade end wall inflow channel and a blade end wall outflow channel, which are arranged in the blade end wall; an outlet of the blade end wall inflow channel is in communication with the first bottom chamber, and an inlet of the blade end wall outflow channel is in communication with the second bottom chamber.

7. The aero-engine turbine assembly according to claim 6 , wherein the internal flow passage further comprises a turbine rotor disk inflow channel and a turbine rotor disk outflow channel, which are arranged in the turbine rotor disk; an inlet of the turbine rotor disk inflow channel is in communication with the electromagnetic pump system, and an outlet of the turbine rotor disk inflow channel is in communication with an inlet of the blade end wall inflow channel; an outlet of the turbine rotor disk outflow channel is in communication with the radiator and an inlet of the turbine rotor disk outflow channel is in communication with the blade end wall outflow channel.

8. The aero-engine turbine assembly according to claim 6 , wherein the blade end wall inflow channel and the blade end wall outflow channel are bending channels.

9. The aero-engine turbine assembly according to claim 1 , wherein the radiator is a fin radiator.

10. The aero-engine turbine assembly according to claim 1 , wherein the electromagnetic pump system comprises an electromagnetic pump body, an induction power supply stationary component and an induction power supply rotating component; the induction power supply stationary component is annular and fixed on a turbine stator disk; the induction power supply rotating component is annular and fixed on the electromagnetic pump body; the induction power supply rotating component comprises an induction module, and the induction module is electrically connected with the electromagnetic pump body; the induction power supply stationary component comprises a power supply module, and the power supply module supplies power to the induction module by means of electromagnetic induction; the induction module supplies power to the power supply module by means of electromagnetic induction, and transmits electric energy to the electromagnetic pump body to supply power for the electromagnetic pump body.

Assignees

• Univ Beihang

Inventors

• Luo Xiang
• Zhang Zhe
• Liu Dongdong
• Wu Zeyu

Classifications

• H02J50/10

  using inductive coupling · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• F01D5/082

  on the side of the rotor disc · CPC title

• F01D5/087

  in the radial passages of the rotor disc · CPC title

• F01D5/088

  in a closed cavity · CPC title