High-radiation coating applied to outer wall surface of rhenium-iridium engine combustion chamber

A high radiation coating and engine technology, applied in the field of high radiation coating, can solve the problems of poor heat dissipation capacity, reduced thrust chamber working life, high temperature of engine thrust chamber, etc., to improve reliability, improve radiation heat dissipation capacity, reduce The effect of wall temperature

Active Publication Date: 2015-03-25
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, when iridium is used as a coating on the outer wall of the rhenium combustor, its radiation coefficient is only 0.1-0.3, and the heat dissipation capacity is poor, which may easily cause the temperature of the thrust chamber of the engine to be high, thereby reducing the working life of the thrust chamber

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] The present invention prepares the high-radiation coating on the outer surface of the rhenium-iridium engine combustion chamber, which adopts the following steps:

[0021] Step (1), powder mixing

[0022] (1) Use 300 mesh sieve to screen HfO 2 Powder 750g;

[0023] (2) Use 300 mesh sieve to screen Pr 6 o 11 Powder 250;

[0024] (3) The above two powders are mixed in an alumina crucible.

[0025] Step (2), powder roasting

[0026] (1) Place the crucible with the powder in a sintering furnace heated to 1300°C for 10 minutes;

[0027] (2) After roasting, the powder is poured into a ball mill jar equipped with agate balls, and the ball mill jar is placed on a ball mill for ball milling for 2 hours;

[0028] (3) After ball milling, the powder is first sieved through a 200-mesh sieve, and then the under-sieve powder is selected after passing through a 400-mesh sieve, and used as the powder for plasma spraying.

[0029] Step (3), coating spraying

[0030] (1) The powd...

Embodiment 2

[0039] The present invention prepares the high-radiation coating on the outer surface of the rhenium-iridium engine combustion chamber, which adopts the following steps:

[0040] Step (1), powder mixing

[0041] (1) Use 300 mesh sieve to screen HfO 2 Powder 800g;

[0042] (2) Use 300 mesh sieve to screen Pr 6 o 11 Powder 200g;

[0043] (3) The above two powders are mixed in an alumina crucible.

[0044] Step (2), powder roasting

[0045] (1) Place the crucible with the powder in a sintering furnace heated to 1350°C for 8 minutes;

[0046] (2) After roasting, the powder is poured into a ball mill jar equipped with agate balls, and the ball mill jar is placed on a ball mill for ball milling for 2 hours;

[0047] (3) After ball milling, the powder is first sieved through a 200-mesh sieve, and then the under-sieve powder is selected after passing through a 400-mesh sieve, and used as the powder for plasma spraying.

[0048] Step (3), coating spraying

[0049] (1) The powd...

Embodiment 3

[0058] The present invention prepares the high-radiation coating on the outer surface of the rhenium-iridium engine combustion chamber, which adopts the following steps:

[0059] Step (1), powder mixing

[0060] (1) Use 300 mesh sieve to screen HfO 2 Powder 900g;

[0061] (2) Use 300 mesh sieve to screen Pr 6 o 11 Powder 100g;

[0062] (3) The above two powders are mixed in an alumina crucible.

[0063] Step (2), powder roasting

[0064] (1) Place the crucible with the powder in a sintering furnace heated to 1400°C for 5 minutes;

[0065] (2) After roasting, the powder is poured into a ball mill jar equipped with agate balls, and the ball mill jar is placed on a ball mill for ball milling for 3 hours;

[0066] (3) After ball milling, the powder is first sieved through a 200-mesh sieve, and then the under-sieve powder is selected after passing through a 400-mesh sieve, and used as the powder for plasma spraying.

[0067] Step (3), coating spraying

[0068] (1) The powd...

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Abstract

The invention relates to a high-radiation coating applied to the outer wall surface of a rhenium-iridium engine combustion chamber. The high-radiation coating is prepared through the steps of preparing mixed powder by taking HfO2 as a main part and Pr6O11 as an additive part through a roasting process; and after ball milling and sieving the mixed powder, preparing the coating on the surface of the combustion chamber with a rhenium-based iridium coating by taking powder with the particle size of 40-80mu m as a plasma spraying raw material through a plasma spraying technology, wherein the key process parameters are as follows: the voltage is 50-70V, the current is 650-750A, the argon flow is 80-100L/min, the hydrogen flow is 10-12L/min, the supply air rate is 30-50g/min, the service life of the prepared coating can be kept for 8 hours at the temperature of 2000 DEG C, and the radiation coefficient is not lower than 0.85. The high-radiation coating is applied to the outer surface of the rhenium-iridium engine combustion chamber, can be used for effectively reducing radiant heat loss and reducing the wall surface temperature of the combustion chamber and is significant in improving the working reliability of an engine.

Description

technical field [0001] The invention relates to a high-radiation coating applied to the outer wall of a rhenium-iridium engine combustion chamber, and belongs to the technical field of surface engineering. Background technique [0002] Small-thrust dual-component liquid rocket engines are mainly used in the attitude and orbit control of space vehicles and strategic and tactical weapons. The fuel combustion temperature in the thrust chamber can reach 2700°C. After adopting the liquid film active cooling technology on the inner wall, the wall temperature is still higher than 1000°C Therefore, in order to ensure the high-temperature strength requirements of the engine thrust chamber, high-temperature refractory metals (Nb, Ta, W, Mo, Re, and platinum, etc.) must be used as body materials, but these materials have poor high-temperature oxidation resistance, such as Niobium alloys will undergo "pest" catastrophic oxidation above 600 °C, and cannot directly face the combustion env...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/12C23C4/10C23C4/11C23C4/134
Inventor 徐方涛张绪虎石刚李海庆贾文军贾中华杨振晓马康智
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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