CN-121802353-B - Gas phase infiltration device applied to turbine blade

CN121802353BCN 121802353 BCN121802353 BCN 121802353BCN-121802353-B

Abstract

Embodiments of the present disclosure disclose a vapor infiltration apparatus applied to turbine blades. The device comprises a lower base, a preheating chamber, a transition supporting seat, a multi-stage gas distribution chamber and an upper base, wherein the lower base, the preheating chamber, the transition supporting seat, the multi-stage gas distribution chamber and the upper base are coaxially arranged, the lower base is connected with an air inlet pipeline, mixed gas circulates in the air inlet pipeline, the preheating chamber is arranged at the top end of the lower base, aluminum particles are contained in the preheating chamber, the mixed gas enters the preheating chamber through the lower base to react with the aluminum particles to form process gas, the transition supporting seat is arranged at the top end of the preheating chamber, the multi-stage gas distribution chamber is arranged at the top end of the transition supporting seat and is connected with the preheating chamber, turbine blades are fixed in the multi-stage gas distribution chamber, the upper base is arranged at the top end of the multi-stage gas distribution chamber, air outlet holes are formed in the upper base, and the process gas permeates into the surface of the turbine blades through the multi-stage gas distribution chamber and is finally discharged through the air outlet holes. This embodiment can improve production efficiency.

Inventors

QIAN YUANJI
ZHENG JIANLIN
JIN HAOTIAN
TANG KAI
NIU XINLEI

Assignees

江苏源清动力技术有限公司

Dates

Publication Date: 20260512
Application Date: 20260306

Claims (8)

1. The gas phase infiltration device applied to the turbine blade is characterized by comprising a lower base, a preheating chamber, a transition supporting seat, a multi-stage gas distribution chamber and an upper base which are coaxially arranged; The lower base is connected with an air inlet pipeline, and mixed gas circulates in the air inlet pipeline; The preheating chamber is arranged at the top end of the lower base, aluminum particles are contained in the preheating chamber, and the mixed gas enters the preheating chamber through the lower base to react with the aluminum particles to form process gas; the transition supporting seat is arranged at the top end of the preheating chamber, and the multi-stage gas distribution chamber is arranged at the top end of the transition supporting seat and is connected with the preheating chamber; The inside of the multistage gas distribution chamber comprises at least one gas distribution seat and at least one blade base, the gas distribution seat comprises a distribution base and a distribution disc, the distribution disc is provided with a gas passing hole array, the distribution disc is embedded into the inside of the distribution base, the blade base is arranged at the top end of the distribution base and is provided with a blade mounting groove corresponding to the gas passing hole array, the edge position of the blade mounting groove is provided with a gas dividing hole array, and the turbine blades are fixed through the blade mounting groove; The upper base is arranged at the top end of the multi-stage gas distribution chamber, the upper base is provided with an air outlet, and the process gas permeates into the surface of the turbine blade through the multi-stage gas distribution chamber and is finally discharged through the air outlet.
2. The vapor infiltration device for use with a turbine blade according to claim 1, wherein the lower base comprises a flange, a gas guide base, a first sleeve, and a bottom plate; The flange is horizontally arranged, one end of the air guide base penetrates through the flange and is connected with the air inlet pipe, the first sleeve is arranged on the flange and is coaxially sleeved outside the air guide base, and the bottom plate is arranged at the top end of the first sleeve; The other end of the air guide base penetrates through the bottom plate to be connected with the preheating chamber.
3. The vapor infiltration device for use with turbine blades according to claim 1, wherein the preheating chamber comprises a second sleeve and an aluminum generator nested within the second sleeve; The aluminum particles are arranged in the aluminum generator.
4. The gas permeation device for use with turbine blades according to claim 1, wherein said multi-stage gas distribution chamber further comprises at least one third sleeve; the third sleeve is arranged at the top end of the blade base, and the turbine blade is arranged inside the third sleeve.
5. The gas permeation device for a turbine blade according to claim 4, wherein said multi-stage gas distribution chamber further comprises a blade tooling, said blade tooling being capable of being embedded within said blade mounting slot; the bottom of the turbine blade is embedded into the blade tool to be fixed.
6. The vapor infiltration device for turbine blades of claim 1, wherein each structural member of the vapor infiltration device is made of graphite material.
7. The vapor infiltration device for a turbine blade according to claim 1, further comprising a protective ring, a thermocouple, and a heat generating shroud; The protection ring is arranged at the top end of the lower base, and the preheating chamber is nested in the protection ring; One end of the thermocouple is embedded into the protection ring, and the other end of the thermocouple extends to the upper base; The heating cover covers the vapor infiltration device, the heating cover can provide a heat source for the vapor infiltration device, and the thermocouple can detect the temperature in the heating cover.
8. The vapor infiltration device for turbine blades as set forth in claim 1, further comprising a cap; the top of the upper base is provided with an annular sealing groove, the air outlet hole and the annular sealing groove are coaxially arranged, and fine sand is placed in the annular sealing groove; the top cover is provided with an annular boss matched with the annular sealing groove, the width of the annular sealing groove is larger than that of the annular boss, and the annular boss can be embedded into fine sand in the annular sealing groove; After the top cover is installed, the height of the fine sand is consistent with the height of the annular sealing groove; and the process gas passes through the gas outlet hole and is discharged through fine sand between the annular boss and the annular sealing groove.

Description

Gas phase infiltration device applied to turbine blade Technical Field The embodiment of the disclosure relates to the technical field of high-temperature protective coating preparation, in particular to a gas permeation device applied to turbine blades. Background Turbine blades need to operate stably for long periods of time in extremely high temperature, high pressure and oxidizing/corrosive environments, and therefore performance treatment of the blade surface is critical. The gas phase infiltration technology is widely applied to improving the wear resistance, corrosion resistance, high temperature stability and other key performances of turbine blades as an advanced surface treatment technology. At present, a common vapor infiltration process is to put the blade to be treated and solid raw materials (such as aluminum particles) required for generating active gas together in a monolithic reaction vessel, and react in the vessel and flow through the surface of the blade to realize coating deposition. However, it has been found in practice that when the above-described method is used for gas-phase infiltration treatment, the active gas is difficult to uniformly distribute when flowing through the stacked blades, resulting in poor uniformity of the thickness of the coating on the surfaces of the blades, and at the same time, the slag generated in the reaction vessel is spread over the inner cavity of the vessel, and the device must be completely disassembled during subsequent cleaning, which is cumbersome and time-consuming, resulting in long equipment downtime and often lower production efficiency. The above information disclosed in this background section is only for enhancement of understanding of the background of the inventive concept and, therefore, may contain information that does not form the prior art that is already known to those of ordinary skill in the art in this country. Disclosure of Invention The disclosure is in part intended to introduce concepts in a simplified form that are further described below in the detailed description. The disclosure is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used to limit the scope of the claimed subject matter. Some embodiments of the present disclosure propose a gas infiltration apparatus applied to turbine blades to address one or more of the technical problems mentioned in the background section above. Some embodiments of the disclosure provide a gas permeation device applied to turbine blades, the device comprises a lower base, a preheating chamber, a transition supporting seat, a multistage gas distribution chamber and an upper base, wherein the lower base is coaxially arranged, the lower base is connected with an air inlet pipeline, mixed gas circulates in the air inlet pipeline, the preheating chamber is arranged at the top end of the lower base, aluminum particles are contained in the preheating chamber, the mixed gas enters the preheating chamber through the lower base to react with the aluminum particles to form process gas, the transition supporting seat is arranged at the top end of the preheating chamber, the multistage gas distribution chamber is arranged at the top end of the transition supporting seat and is connected with the preheating chamber, the multistage gas distribution chamber comprises at least one gas distribution seat and at least one blade base, the gas distribution seat comprises a distribution base and a distribution disc, the distribution disc is embedded in the distribution base, the blade base is arranged at the top end of the distribution base and is provided with a blade mounting groove corresponding to the air through holes array, the blade mounting groove corresponding to the air through the air holes is arranged at the blade mounting groove, the gas permeation groove is arranged at the top end of the multistage gas distribution chamber through the turbine blade mounting groove, and the gas permeation groove is arranged at the top end of the multistage gas distribution chamber through the air outlet groove is arranged at the top end of the turbine blade mounting groove. Optionally, the lower base comprises a flange, an air guide base, a first sleeve and a bottom plate, wherein the flange is horizontally arranged, one end of the air guide base penetrates through the flange to be connected with the air inlet pipe, the first sleeve is arranged on the flange and coaxially sleeved outside the air guide base, the bottom plate is arranged at the top end of the first sleeve, and the other end of the air guide base penetrates through the bottom plate to be connected with the preheating chamber. Optionally, the preheating chamber comprises a second sleeve and an aluminum generator, wherein the aluminum generator is nested in the second sleeve, and the aluminum particles are arranged in the aluminum generator. Optionally, the multi-stage gas distribution ch