高度
-英尺
羅爾斯-羅伊斯公司的對轉(zhuǎn)風(fēng)扇發(fā)動機(jī)
（方案）
“薩菲爾”（Sapphire）和“梅特羅維克”（Metrovick）F9飛機(jī)的研制工作一起于l946年開始，當(dāng)梅特羅波里頓-維克斯（Metropolitan-Vickers）于1947年從航空界退出后轉(zhuǎn)交給阿姆斯特朗-西德利公司。“薩菲尓”發(fā)動機(jī)于1948年10月首次運轉(zhuǎn)，先后在“彗星（Meteor）、“哈斯汀斯”（Hastings）和“堪培拉”（Canberra）飛機(jī)上作過飛行試驗，然后投入批生產(chǎn)，用于格洛斯特公司的“標(biāo)槍”（Gloster Javelin）和霍克公司的“獵人”（Hawker Hunter)F2飛機(jī)。

The Sapphire originated in 1946 with the Metrovick F9, which was handed over to Armstrong-Siddeley when Metropolitan-Vickers withdrew from aviation in 1947. The Sapphire first ran in October 1948 and the engine was flight tested in Meteor, Hastings and Canberra aircraft; before going into production for the Gloster Javelin and Hawker Hunter F2.
阿姆斯特朗-西德利公司的
“薩菲爾”發(fā)動機(jī)
Armstrong Siddeley Sapphire

12: Controls and instrumentation

目  錄
Contents  Page
Introduction 133
Controls 133
緒言
控制器
儀表
Instrumentation 135

Engine thrust Engine torque Engine speed Turbine gas temperature Oil temperature and pressure Fuel temperature and pressure Fuel flow Vibration Warning systems Aircraft integrated data system   發(fā)動機(jī)推力
  發(fā)動機(jī)扭矩
  發(fā)動機(jī)轉(zhuǎn)速
  渦輪燃?xì)鉁囟?br />   滑油溫度和壓力
  燃油溫度和壓力
  燃油流量
  振動
  警告系統(tǒng)
  飛機(jī)綜合數(shù)據(jù)系統(tǒng)
  電子指示系統(tǒng)
Electronic indicating systems
同步和同相
Synchronizing and synchrophasing 144
manually controlled by the pilot selecting the desired thrust setting and monitoring the instruments to maintain the engine within the relevant operating limitations.
3. The multitude of dials and gauges on the pilot's instrument panel may be replaced by one or a

INTRODUCTION  number of cathode ray tubes to display engine parameters. These are small screens capable of
1. The controls of the gas turbine engine are

displaying all of the information necessary to operatedesigned to remove, as far as possible, work load
the engine safely. from the pilot while still allowing him ultimate control of the engine. To achieve this, the fuel flow is auto-CONTROLS matically controlled after the pilot has made the initial 4. The control of a gas turbine engine generally
power selection (Part 10). requires the use of only one control lever and the
2. All engine parameters require monitoring and monitoring of certain indicators located on the pilot's instrumentation is provided to inform the pilot of the instrument panel (fig. 12-1). Operation of the control correct functioning of the various engine systems (throttle/power) lever selects a thrust level which is and to warn of any impending failure. Should any of then maintained automatically by the fuel system the automatic governors fail, the engine can be (Part 10).
第十二章 控制器和儀表
3．駕駛員儀表板上的許多盤式和指針式儀表可以
由一個或幾個陰極射線管來取代，用來顯示發(fā)動機(jī)
的各種參數(shù)。這些小型視屏能夠顯示使發(fā)動機(jī)安全
工作所必須的所有信息。
控制器

4．燃?xì)鉁u輪發(fā)動機(jī)的控制通常要求只用一根操縱桿并且監(jiān)視位于駕駛員儀表板(圖12-1)上的某些指示器。用操縱桿(油門／功率)選擇某個推力水平之后，這個推力水平就由燃油系統(tǒng)(第l0章)自動保持。
Controls and instrumentation

圖12-1 駕駛員的儀表板-渦輪噴氣發(fā)動機(jī)
5．對于裝有加力燃燒室的發(fā)動機(jī)，仍保持使用一根操縱桿的控制，但是需用另一個燃油系統(tǒng)來供應(yīng)及控制給加力燃燒室的燃油。
 
6．對于渦輪螺槳發(fā)動機(jī)，油門桿和螺旋槳控制裝置是聯(lián)動的，因而保持用一根桿操縱發(fā)動機(jī)。同樣，直升機(jī)的油門控制桿與總距操縱桿是聯(lián)動的，所以能保證槳距增加時同時增大發(fā)動機(jī)功率。
Controls and instrumentation

5. On engines fitted with afterburning, single lever control is maintained, although a further fuel system is required to supply and control the fuel to the afterburner (Part 16). 儀表板

6.
On a turbo-propeller engine, the throttle lever is interconnected with the propeller control unit (P.C.U.), thus maintaining single lever operation of the engine. Similarly, the throttle control lever of a helicopter is interconnected with the collective pitch lever, so ensuring that an increase in pitch is accompanied by an increase in engine power,

7.
The fuel system (Part 10) incorporates a high pressure fuel shut-off cock to provide a means of stopping the engine. This may be operated by a separate lever, interconnected with the throttle lever, or electrically actuated and controlled by a switch on the pilot's instrument panel.

8.
A turbo-jet engine fitted with a thrust reverser usually has an additional control lever that allows reverse thrust to be selected (Part 15). On a turbo-propeller engine, a separate control lever is not required because the interconnected throttle and
　
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