CN-121994988-A - Rotor blade titanium fire test device and test method based on laser spot fire method

Abstract

A titanium fire test device for a rotor blade based on a laser ignition method is provided, and comprises a laser, a shell and a driving assembly, wherein the shell defines a cavity for accommodating the rotor blade, a transmission window is arranged on the shell and is used for receiving laser generated by the laser so as to ignite the rotor blade, and the driving assembly comprises a rotating shaft connected with the rotor blade and a motor for driving the rotating shaft to rotate in the cavity. A method for testing titanium fire of a rotor blade is also provided. The device can truly simulate the splashing of high-temperature particulate matters of the titanium fire.

Inventors

• DING LIANG
• XU FENG
• QIN WEN
• HOU NAIXIAN
• WU ZHIQING
• YOU YULONG

Assignees

• 中国航发商用航空发动机有限责任公司

Dates

Publication Date

20260508

Application Date

20241107

Claims (18)

1. 1. Rotor blade titanium fire test device based on laser spot fire method includes: A laser; A housing defining a chamber for receiving the rotor blade, the housing having a transmissive window for receiving laser light generated by the laser to ignite the rotor blade; characterized by further comprising: the driving assembly comprises a rotating shaft connected with the rotor blade and a motor for driving the rotating shaft and is used for driving the rotor blade to rotate in the cavity.
2. 2. The test device of claim 1, further comprising a companion blade positioned within the chamber and disposed axially adjacent to the rotor blade.
3. 3. The test device of claim 1, wherein the rotor blade is a titanium rotor dummy blade.
4. 4. The test device of claim 2, wherein the outer surface of the housing is provided with a vane mounting base, and the crank of the accompanying blade passes through the housing and the vane mounting base and is fixed.
5. 5. The test device of claim 2, wherein the companion blade is a titanium alloy or an alloy steel.
6. 6. The test device of claim 2, wherein the companion blade and/or the rotor blade surface is sprayed with a flame retardant coating.
7. 7. The test device of claim 1, wherein the housing comprises a case simulation section, the case simulation section being of a titanium alloy material or an alloy steel material.
8. 8. The test device of claim 7, wherein the inner surface of the receiver simulation segment is sprayed with a flame retardant coating or a flame retardant-free coating.
9. 9. The test device of claim 1, wherein the housing comprises a transition section and a measurement section, the transition section being tapered, comprising a transition section outside and a transition section inside, the motor being located inside the transition section, the shaft being located within the measurement section.
10. 10. The test device of claim 1, further comprising a sensing assembly comprising a temperature sensor and a pressure sensor.
11. 11. The test device of claim 10, wherein the temperature sensor and the pressure sensor are disposed proximate the transmission window.
12. 12. The test device according to claim 1, wherein the rotor blade is made of one of a Ti17 titanium alloy, a TC4 titanium alloy, a Ti8Al1Mo1V titanium alloy, a Ti-Cu-Al flame retardant titanium alloy, and a Ti-V-Cr flame retardant titanium alloy.
13. 13. The test device of claim 1, further comprising a gas source for supplying a high temperature, high velocity gas stream to the chamber.
14. 14. A method of titanium fire testing of rotor blades, characterized in that it is carried out using a test device according to any one of claims 1-10, the method comprising the steps of: supplying high-temperature high-speed airflow to the chamber until the inside of the chamber reaches a pneumatic stable state; Starting a motor to drive the rotating shaft and the rotor blades to rotate; Starting a laser to enable laser to penetrate through the transmission window to the surface of the rotor blade, so that the rotor blade is ignited; After the combustion is finished, titanium fire analysis is carried out.
15. 15. The method of claim 14, further comprising a companion blade positioned within the chamber, wherein an original weight of the rotor blade and/or companion blade is recorded prior to initiation of the test, wherein a post-ablation weight of the rotor blade and/or companion blade is recorded after combustion is completed, and wherein the ablation rate is calculated using the original weight and the post-ablation weight.
16. 16. The method of claim 14, wherein the supply of high temperature, high velocity air flow is stopped within 15s to 30s after the rotor blade is ignited, and the motor is turned off.
17. 17. The method of claim 14, further comprising a companion blade positioned within the chamber, wherein the titanium fire analysis further comprises splash damage of the shell, companion blade by titanium fire high temperature particulate matter.
18. 18. The method of claim 14, wherein the analysis of the titanium fire further comprises analysis of extent of ablation, analysis of flame retardant effect of the flame retardant coating, analysis of flame retardant properties of the flame retardant titanium alloy.

Description

Rotor blade titanium fire test device and test method based on laser spot fire method Technical Field The invention relates to the field of test devices, in particular to the field of titanium fire tests of blades. Background Titanium alloys are often used in compressor structures, but titanium alloys are burnt by firing under severe impact and friction conditions, so that a titanium fire test is necessary. The compressor is in a state of high-speed rotation in actual work and is in a high-temperature and high-speed airflow environment. Titanium fire high-temperature particles can be generated after the titanium alloy is combusted, and the titanium fire high-temperature particles are splashed under the comprehensive actions of rotating centrifugal force and high-speed air flow to generate splash damage. Disclosure of Invention The invention aims to provide a rotor blade titanium fire test device based on a laser spot fire method, which can truly simulate the splashing of high-temperature particles of titanium fire. The titanium fire test device for the rotor blade comprises a laser, a shell and a driving assembly, wherein the shell defines a cavity for accommodating the rotor blade, a transmission window is formed in the cavity and is used for receiving laser generated by the laser to ignite the rotor blade, and the driving assembly comprises a rotating shaft connected with the rotor blade and a motor for driving the rotating shaft and is used for driving the rotor blade to rotate in the cavity. In one or more embodiments, the apparatus further includes a companion blade positioned within the chamber, disposed axially adjacent to the rotor blade. In one or more embodiments, the rotor blade is a titanium rotor simulation blade. In one or more embodiments, the outer surface of the housing is provided with a vane mounting base, and the crank of the accompanying blade passes through the housing and the vane mounting base and is fixed. In one or more embodiments, the companion blade is a titanium alloy material or an alloy steel material. In one or more embodiments, the companion blade and/or the rotor blade surface is sprayed with a flame retardant coating. In one or more embodiments, the housing includes a case simulation section that is a titanium alloy material or an alloy steel material. In one or more embodiments, the inner surface of the case simulation segment is sprayed with a flame retardant coating or a flame retardant-free coating. In one or more embodiments, the housing includes a transition section and a measurement section, the transition section is tapered, including a transition section outside and a transition section inside, the motor is located inside the transition section, and the shaft is located within the measurement section. In one or more embodiments, the apparatus further includes a sensing assembly including a temperature sensor and a pressure sensor. In one or more embodiments, the temperature sensor and the pressure sensor are disposed proximate to the transmission window. In one or more embodiments, the rotor blade is made of one of Ti17 titanium alloy, TC4 titanium alloy and Ti8Al1Mo1V titanium alloy, or one of Ti-Cu-Al flame retardant titanium alloy and Ti-V-Cr flame retardant titanium alloy. In one or more embodiments, the test device is further provided with a gas source for supplying a high temperature, high velocity gas stream to the chamber. The invention further aims to provide a titanium fire test method for the rotor blade by using the test device, which comprises the steps of supplying high-temperature high-speed airflow to a cavity until the cavity reaches a pneumatic stable state, starting a motor to drive a rotating shaft and the rotor blade to rotate, starting a laser to enable the laser to penetrate a transmission window to the surface of the rotor blade so that the rotor blade is ignited, and carrying out titanium fire analysis after combustion is finished. In one or more embodiments, the apparatus further comprises a companion blade positioned within the chamber, the original weight of the rotor blade and/or companion blade is recorded before the start of the test, the post-ablation weight of the rotor blade and/or companion blade is recorded after the end of the combustion, and the ablation rate is calculated using the original weight and the post-ablation weight. In one or more embodiments, the supply of the high-temperature high-speed air flow is stopped within 15 s-30 s after the rotor blade is ignited, and the motor is turned off. In one or more embodiments, the apparatus further comprises a companion blade positioned within the chamber, and the titanium fire analysis further comprises splash damage of the housing, companion blade by titanium fire high temperature particulate matter. In one or more embodiments, the titanium fire analysis further includes ablation degree analysis, flame retardant effect analysis of a flame retardant coating, flame retardant p