羅爾斯-羅伊斯公司
“康維”（Conway）發動機
Rolls-Royce Conway
Rolls-Royce RM60
RM60發動機是按英國海軍部要求設計的，這是具有良好巡航經濟性的 發動機。雖然它是以航空發動機為基礎，但從開始就是作為船用燃氣發動機設計的。兩臺RM60發動機于1953年在以前的蒸汽發動機炮艇HMS Grey Goose號上下海。這是世界上第一艘以燃氣渦輪發動機為動力的戰艦。
Produced in response to an Admiralty contract for a coastal-craft engine with good cruising economy, the RM60, although based on aeroengine philosophy, was designed from the first as a marine gas turbine. Two RM60s went to sea in 1953 in the former steam gunboat HMS Grey Goose, the world's first warship to be powered solely by gas turbines.
羅爾斯-羅伊斯公司
RM60發動機
20: Thrust distribution
第二十章 推力分布
INTRODUCTION
緒言
推力分布
計算推力的方法
發動機推力計算
壓氣機機匣
擴散器涵道
燃燒室
渦輪裝置
排氣袋置和噴管
推進噴管
發動機
傾斜燃燒室
加力燃燒
推力分布
2．圖20-1是一種典型的單轉子軸流式渦輪噴氣發動機，表示了主要的向前的和向后的力作用于何處。用第2章表示的發動機工作循環可解釋這些力的來源。
1. Although the principles of jet propulsion (see Part 1) will be familiar to the reader, the distribution of the thrust forces within the engine may appear somewhat obscure- These forces are in effect gas loads resulting from the pressure and momentum changes of the gas stream reacting on the engine structure and on the rotating components. They are in some locations forward propelling forces and in others opposing or rearward forces. The amount that
Contents
Introduction Distribution of the thrust forces Method of calculating the thrust forces Calculating the thrust of the engine
Compressor casing Diffuser duct Combustion chambers Turbine assembly Exhaust unit and jet pipe Propelling nozzle Engine Inclined combustion chambers
Afterburning
Page 207 207 209 209
212
緒言
1．雖然噴氣推進原理(見第1章)對讀者來說可能是熟悉的。但是，對發動機內部的推力分布可能會有點不太清楚。這些力實際上是燃氣流的壓力和動量變化導致的氣體載荷對發動機結構件和轉動部件產生的反作用力。在一些位置，它們是向前的推進力，在另外一些地方，則是相反的即向后的力。向前的力的總和超過向后的力的總和的總額通常被稱作發動機的額定推力。
the sum of the forward forces exceeds the sum of the rearward forces is normally known as the rated thrust of the engine.
DISTRIBUTION OF THE THRUST FORCES
2. The diagram in fig. 20-1 is of a typical single-spool axial flow turbo-jet engine and illustrates where the main forward and rearward forces act. The origin of these forces is explained by following the engine working cycle shown in Part 2.
207
3.在喜歡開始時，空氣被吸入發動機并被壓縮。通過壓氣機各級的向后加速和總的壓力升高產生一個很大的向前的反作用力。在空氣流程的下一步，空氣通過擴壓氣。它在這里產生一個小的反作用力，方向也向前。
5.當膨脹的燃氣離開燃燒室和流經導向器葉片時，它們被加速并偏轉到渦輪的工作葉片上（第5章）。由于燃氣流的加速和偏轉，加上后來進入噴管時變直，就產生了相當大的“阻力”；因而靜止葉片和轉動葉片都受到很大的向后的力，其大小可在圖中看出。當燃氣流通過排氣系統（第6章）時，較小的向前的力可作用于內錐或尾錐上。但一般來說，只產生向后的力，它們是由于燃氣流在推進噴管中的“阻力”所致。
6.可以看到，在空氣通過發動機時，其速度和壓力會發生變化（第2章）。例如，在需要將速度（動）能轉換成壓力能的地方，通道呈擴散形，與用于壓氣機擴壓器上的形狀類似。相反，在需要將儲存在燃燒后的燃氣中的能量轉換成速度的地方，就采用與渦輪中類似的收斂通道或噴管。在轉換成速度能的地方，就產生“阻力”載荷或向后的力；在轉換成壓力能的地方，就產生向前的力。第2章中的圖2-3表示了發動機上這兩處的速度和壓力變化。
Thrust distribution
圖20-1 一種典型的單轉子軸流式發動機的推力分布
Fig. 20-1 Thrust distribution of a typical single-spool axial flow engine.
排氣裝置
和噴管
燃燒室
渦輪
擴壓器
壓氣機
推進噴管
4.空氣從擴壓氣進入燃燒室（第4章），在那里受到加熱。氣體在后來的膨脹和加速中，在燃燒室壁上作用有很大的向前的力。
向后的燃氣載荷46，678磅
向前的燃氣載荷57，836磅
3.
At the start of the cycle, air is induced into the engine and is compressed. The rearward accelera-tions through the compressor stages and the resultant pressure rise produces a large reactive force in a forward direction. On the next stage of its journey the air passes through the diffuser where it exerts a small reactive force, also in a forward direction,
4.
From the diffuser the air passes into the combustion chambers (Part 4) where it is heated, and in the consequent expansion and acceleration of the gas large forward forces are exerted on the chamber walls.
5.
When the expanding gases leave the combustion chambers and flow through the nozzle guide vanes they are accelerated and deflected on to the blades of the turbine (Part 5). Due to the acceleration and deflection, together with the subsequent straighten-ing of the gas flow as it enters the jet pipe, consider-able 'drag' results; thus the vanes and blades are subjected to large rearward forces, the magnitude of
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