发明名称 |
Control system |
摘要 |
A control apparatus 50 for a gas turbine engine for an aircraft includes engine control means 52 forming part of an outer fuel control loop and fuel control means/overthrust protector 76 forming part of an inner fuel control loop. Overthrust protection is provided within each of the engine control means 52 and the fuel control means/overthrust protector 76, which are powered and housed separately. Thus, a failure within one of these systems could not result in overthrust and demonstrably reliable overthrust protection is provided within a single channel.
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申请公布号 |
US2004139727(A1) |
申请公布日期 |
2004.07.22 |
申请号 |
US20030679262 |
申请日期 |
2003.10.07 |
申请人 |
HORSWILL MICHAEL A.;GARNER STEPHEN G. |
发明人 |
HORSWILL MICHAEL A.;GARNER STEPHEN G. |
分类号 |
F02C9/28;F02C9/46;F02C9/48;(IPC1-7):F02K3/00 |
主分类号 |
F02C9/28 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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