Medium bypass turbofan engine
A gas turbine engine of the turbofan type is described which consists of: A. a generally tubular axially extending housing assembly defining a radially outer annular bypass duct extending from the inlet end of the housing assembly to the exhaust end thereof; B. an annular burner positioned within the housing assembly radially inwardly of the bypass duct and concentric to the central axis of the housing assembly; C. a low pressure spool assembly including a first shaft journaled on the central axis of the housing assembly, a fan on the first shaft disposed proximate the inlet end of the housing assembly, and a low pressure turbine on the first shaft disposed proximate the exhaust end of the housing assembly; and D. a high pressure spool assembly including a hollow second shaft telescopically received over the first shaft, a high pressure compressor on the second shaft positioned between the fan and the burner, a high pressure turbine on the second shaft positioned between the burner and the low pressure turbine, and an annular rotary slinger on the second shaft positioned between the high pressure compressor and the high pressure turbine and arranged to sling fuel radially outwardly into the burner.
- Assignee:
- Williams International Corp., Walled Lake, MI
- Patent Number(s):
- US 4598544
- OSTI ID:
- 5588445
- Resource Relation:
- Patent File Date: Filed date 28 Apr 1983
- Country of Publication:
- United States
- Language:
- English
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