| 摘要 |
<p>A gas turbine engine (10) comprises an outer engine case (12), a combustor (16), a high pressure spool (18) and a low pressure spool (20). The combustor (16) is disposed within the outer engine case (12). The high pressure spool (18) is configured for rotation coaxially with the combustor. The low pressure spool (20) is configured for rotation coaxially with the high pressure spool (18). The low pressure spool (20) is configured to rotate at speeds faster than that of the high pressure spool (18) during operation of the gas turbine engine. In one embodiment, the low pressure spool (20) includes a gear system (108) configured to rotate a low pressure compressor (124) faster than a low pressure turbine (126). In another embodiment, the high pressure spool (18) rotates outward of the combustor within the outer engine case (12). In another embodiment, the high pressure spool (18) includes a drum (84) having radially inward projecting blades and vanes and radially outward projecting fan blades.</p> |
