可调喷口
供氧和供油
图1-12 一种涡轮-火箭发动机
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.涡轮-火箭发动机(图1-12)可视为涡轮/冲压喷气发动机的代用发动机；然而，一个重要的差异在于它自备燃烧用的氧。
21.这种发动机有一多级涡轮驱动的低压压气机；而驱动涡轮的功率是在火箭型燃烧室中燃烧煤油和液氧产生的。因为燃气温度将在3500℃的量级，在燃气进入涡轮前额外的燃油喷入燃烧室以供冷却。然后，这种富油混合气（燃气）用压气机流来的空气稀释，残余的燃油在常规加力系统中燃烧。
22.虽然这种发动机比涡轮/冲压喷气发动机小而且轻，但是，其耗油更高。这种趋势使它比较适合截击机或者空间发射器型飞机。这些飞机要求高空高速性能，通常具有完全加速和续航时间很短的发行计划。
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.
罗尔斯-罗伊斯／法国国营航空发动机研究制造公司的“奥林普斯”(Olympus)发动机
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.
回流式动力喷气(Power Jet）W2B的通流型称为W2B/26，是由Rover Company于1941至l943的。罗尔斯-罗伊斯公司于1943年接管，重新命名为“德温特”(Derwent)。1943年11月通过了2000磅推力100小时试验，并于1944年4月以同等推力飞行。该发动机作为格洛(Gloster)公司的“流星III”(Meteor III)的动力，1945年投入使用。
罗尔斯-罗伊斯公司RB37“德温特l”发动机
2: Working cycle and airflow
第二章 工作循环和气流
Contents 目录 页码
绪言 11
工作循环 11
压力、体积和温度间的关系 l3
速度和压力变化 14
气流 17
Page
Introduction 11
Working cycle 11
The relations between pressure, volume and temperature 13 Changes in velocity and pressure 14 Airflow 17
1．燃气涡轮发动机本质上是一种热力发动机，用空气作为提供推力的工作流体。为达此目的，必须将通过发动机的空气加速；这意味着增加空气的速度即动能。为了达到这种增加，首先要增加压力能，继之加入热能，最后，再以高速喷气流的形式转变成动能。
绪言
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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