File:Bristol Olympus preliminary configurations 1945-1946.svg

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English: Alternative configurations (A-D) studied by Bristol Engine Division for a new high thrust turbojet (1945-1946). "D" is the final scheme that led to B.E.10 Olympus turbojet.

1)LP axial compressor 2)HP centrifugal compressor 3)Combustion chambers 4)HP turbine 5)LP turbine 6)HP spool 7)LP spool 8)HP axial compressor 9)Axial compressor (single section) 10)Turbine (single stage)

11)Single spool
Italiano: Studi preliminari Della Bristol Engine Division per un turbogetto ad alta spinta (anni 1945-1946). La "D" è lo schema definitivo adottato alla base della versione B.E.10 Olympus.

1)Compressore assiale di bassa pressione 2)Compressore centrifugo di alta pressione 3)Camere di combustione 4)Turbina di alta pressione 5)Turbina di bassa pressione 6)Albero di alta pressione 7)Albero di bassa pressione 8)Compressore assiale di alta pressione 9)Compressore assiale (singola sezione) 10)Turbina (singolo stadio)

11)Albero motore
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Author Nubifer

Based on drawings found on Flight International article

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current10:15, 19 April 2011Thumbnail for version as of 10:15, 19 April 2011437 × 644 (136 KB)Nubifer (talk | contribs){{Information |Description ={{en|1=Alternative configurations (A-D) studied by Bristol Engine Division for a new high thrust turbojet (1945-1946). "D" is the final scheme that led to B.E.10 Olympus turbojet. 1)LP axial compressor 2)HP centrifugal comp

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