可調噴口
供氧和供油
圖1-12 一種渦輪-火箭發動機
20.
The turbo-rocket engine (fig. 1-12) could be considered as an alternative engine to the turbo/ram jet; however, it has one major difference in that it carries its own oxygen to provide combustion,
21.
The engine has a low pressure compressor driven by a multi-stage turbine; the power to drive the turbine is derived from combustion of kerosine and liquid oxygen in a rocket-type combustion chamber. Since the gas temperature will be in the order of 3,500 deg. C, additional fuel is sprayed into the
20.渦輪-火箭發動機(圖1-12)可視為渦輪/沖壓噴氣發動機的代用發動機；然而，一個重要的差異在于它自備燃燒用的氧。
21.這種發動機有一多級渦輪驅動的低壓壓氣機；而驅動渦輪的功率是在火箭型燃燒室中燃燒煤油和液氧產生的。因為燃氣溫度將在3500℃的量級，在燃氣進入渦輪前額外的燃油噴入燃燒室以供冷卻。然后，這種富油混合氣（燃氣）用壓氣機流來的空氣稀釋，殘余的燃油在常規加力系統中燃燒。
22.雖然這種發動機比渦輪/沖壓噴氣發動機小而且輕，但是，其耗油更高。這種趨勢使它比較適合截擊機或者空間發射器型飛機。這些飛機要求高空高速性能，通常具有完全加速和續航時間很短的發行計劃。
Basic mechanics
combustion chamber for cooling purposes before the gas enters the turbine. This fuel-rich mixture (gas) is then diluted with air from the compressor and the surplus fuel burnt in a conventional afterburning system.
22. Although the engine is smaller and lighter than the turbo/ram jet, it has a higher fuel consumption. This tends to make it more suitable for an interceptor or space-launcher type of aircraft that requires high speed, high altitude performance and normally has a flight plan that is entirely accelerative and of short duration.
羅爾斯-羅伊斯／法國國營航空發動機研究制造公司的“奧林普斯”(Olympus)發動機
Rolls-Royce/Snecma Olympus
A straight-through version of the reverse-flow Power Jets W2B, known as the W2B/26, was developed by the Rover Company from 1941 to 1943. Taken over by Rolls-Royce in April 1943 and renamed the Derwent, it passed a 100hr. test at 2000 lb thrust in November 1943 and was flown at that rating in April 1944. The engine powered the Gloster Meteor III which
Rolls-Royce RB37 Derwent 1
entered service in 1945.
回流式動力噴氣(Power Jet）W2B的通流型稱為W2B/26，是由Rover Company于1941至l943的。羅爾斯-羅伊斯公司于1943年接管，重新命名為“德溫特”(Derwent)。1943年11月通過了2000磅推力100小時試驗，并于1944年4月以同等推力飛行。該發動機作為格洛(Gloster)公司的“流星III”(Meteor III)的動力，1945年投入使用。
羅爾斯-羅伊斯公司RB37“德溫特l”發動機
2: Working cycle and airflow
第二章 工作循環和氣流
Contents 目錄 頁碼
緒言 11
工作循環 11
壓力、體積和溫度間的關系 l3
速度和壓力變化 14
氣流 17
Page
Introduction 11
Working cycle 11
The relations between pressure, volume and temperature 13 Changes in velocity and pressure 14 Airflow 17
1．燃氣渦輪發動機本質上是一種熱力發動機，用空氣作為提供推力的工作流體。為達此目的，必須將通過發動機的空氣加速；這意味著增加空氣的速度即動能。為了達到這種增加，首先要增加壓力能，繼之加入熱能，最后，再以高速噴氣流的形式轉變成動能。
緒言
INTRODUCTION
1. The gas turbine engine is essentially a heat engine using air as a working fluid to provide thrust. To achieve this, the air passing through the engine has to be accelerated; this means that the velocity or kinetic energy of the air is increased. To obtain this increase, the pressure energy is first of all increased, followed by the addition of heat energy, before final conversion back to kinetic Energy in the form of a high velocity jet efflux.
WORKING CYCLE
2. The working cycle of the gas turbine engine is similar to that of the four-stroke piston engine. However, in the gas turbine engine, combustion occurs at a constant pressure, whereas in the piston engine it occurs at a constant volume. Both engine cycles (fig. 2-1) show that in each instance there is induction, compression, combustion and exhaust. These processes are intermittent in the case of the piston engine whilst they occur continuously in the gas turbine. In the piston engine only one stroke is utilized in the production of power, the others being involved in the charging, compressing and exhausting of the working fluid. In contrast, the turbine engine eliminates the three 'idle' strokes, thus enabling more fuel to be burnt in a shorter time; hence it produces a greater power output for a given size of engine.
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