| 11. | Air passing through the turbojet was compressed further by the remaining 5 compressor stages and then fuel was added in the combustion chamber.
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| 12. | Typically for high speed equipment, as flow increases the velocity of the flow can approach sonic speed somewhere within the compressor stage.
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| 13. | Earlier versions have 7 axial compressor stages mounted on the HP shaft to supercharge a relatively low-pressure-ratio centrifugal compressor.
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| 14. | This implies a higher high-pressure shaft speed, to maintain the datum blade tip Mach number on the rear compressor stage.
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| 15. | The J402-CA-400 was a single-shaft engine, with one axial compressor stage and one centrifugal compressor stage.
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| 16. | The J402-CA-400 was a single-shaft engine, with one axial compressor stage and one centrifugal compressor stage.
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| 17. | Another cooler would be positioned after the second stage, which was the final compressor stage, and that was the " aftercooler ".
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| 18. | At the 13th ( i . e . the final ) compressor stage, air is bled out and used for anti-icing.
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| 19. | The compressor stages have been developed from bearings, oiling systems ) could be merged to the main fueling system running on aviation fuel.
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| 20. | It was proposed that an air-bleed system should be installed after the fifth compressor stage to supply compressed air, if needed.
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