空气燃油比
Rolls-Royce Turbomeca Adour Mk102
罗尔斯-罗伊斯透博梅卡公司
“阿杜尔”(Adour)Mk102发动机
1．工作从1945年1月开始，按“尼恩”发动机以0.855比例缩小，以适合于格洛斯特公司的“流星”(Gloster Meteor)
的发动机短舱中。称为“德温特”(Derwent)的该发动机于1945年6月以2600磅通过了100小时试车，于9月投产，服役时达到3500磅。装了特殊的“德温特’V发动机的“流星”Ⅳ飞机于1945年11月和1946年两项世界速度记录。
Work commenced in January 1945 on a 0.855 scale Nene, reduced to fit the engine nacelle of a Gloster Meteor. Known as the Derwent V the engine passed a 100 hr test at 2600 lb thrust in June 1945 and in September went into production with a service rating of 3500 lb. Two world speed records were set by Meteor IV's powered by special Derwent V's in November 1945 and September 1946.
罗尔斯-罗伊斯公司
RB37“德温特”V发动机
Rolls-Royce RB37 Derwent V
目 录
5: Turbines
Contents Page
第五章 涡轮
Introduction 45 Energy transfer from gas flow to turbine 49 绪言
从燃气流向涡轮的
能量转移
结构
Construction 51
Nozzle guide vanes Turbine discs Turbine blades 导向器叶片
涡轮盘
涡轮工作叶片
对转涡轮
双合金轮盘
Contra-rotating turbines Dual alloy discs
压气机涡轮的匹配
Compressor-turbine matching 53 材料
Materials 53 Nozzle guide vanes Turbine discs 导向器叶片
涡轮盘
涡轮工作叶片
Turbine blades 平衡
Balancing 57
1．涡轮的任务是为驱动压气机和附件提供功率，以及当发动机不单纯用于产生推进喷气流的情况下，它还为螺旋桨或旋冀提供轴功率。涡轮的工作是从燃烧系统释放的燃气流吸收能量，并将就膨胀到较低的压力和温度。在这个过程中产生很高的应力，而且，为了工作效率高，涡轮叶尖可能在高于l500英尺／秒的速度下旋转。涡轮经受的连续燃气流的进口温度可能达到850到1700℃，在涡轮部件中的燃气速度可能达到2500英尺／秒。
绪言
INTRODUCTION
1. The turbine has the task of providing the power to drive the compressor and accessories and, in the case of engines which do not make use solely of a jet for propulsion, of providing shaft power for a propeller or rotor. It does this by extracting energy from the hot gases released from the combustion system and expanding them to a lower pressure and temperature. High stresses are involved in this process, and for efficient operation, the turbine blade tips may rotate at speeds over 1,500 feet per second, The continuous flow of gas to which the turbine is exposed may have an entry temperature between 850 and 1,700 deg. C. and may reach a velocity of over 2,500 feet per second in parts of the turbine.
2．为了产生驱动扭矩，涡轮可以有若干级，每级有 一排静止的导向器叶片和一排旋转的工作叶片(图5-1)。级数取决于需要从燃气流吸收的功率，发出该功率的旋转速度，及允许的涡轮直径。
2. To produce the driving torque, the turbine may consist of several stages each employing one row of stationary nozzle guide vanes and one row of moving blades (fig. 5-1). The number of stages depends upon the relationship between the power required
3.轴的数量，因而涡轮的数量随发动机的型别而异。高压比发动机通常有两根轴，分别驱动高压和低压压气机（图5-2）。对于高涵道比风扇发动机，其以有一个中压系统为特点，则在高压和低压涡轮之间插入另一个涡轮，这就构成了三转子系统（图5-3）在某些发动机上，其驱动扭矩来自由动力涡轮（图5-4）。由于它与其它的涡轮轴和压气机轴在机械上是独立的，所以这种方法允许此涡轮在其最佳的转速下运转。
from the gas flow, the rotational speed at which it must be produced and the diameter of turbine permitted.
3. The number of shafts, and therefore turbines, varies with the type of engine; high compression ratio engines usually have two shafts, driving high and low pressure compressors (fig, 5-2). On high by-pass
图5-1 单轴系统三级涡轮
ratio fan engines that feature an intermediate pressure system, another turbine may be interposed between the high and low pressure turbines, thus forming a triple-spool system (fig, 5-3). On some engines, driving torque is derived from a free-power turbine (fig. 5-4). This method allows the turbine to run at its optimum speed because it is mechanically independent of other turbine and compressor shafts.
4．对于给定的级输出，涡轮工作叶片的平均速度对可能取得的最高效率具有很大的影响。对于给定的输出，燃气速度、转折角、以及损失都随较高的叶片平均速度的平方成比例地减少。涡轮盘的应力随转速的平方而增加，所以要在较高转速下保持相同的应力水平，截面厚度及重量应当不成比例地增加。正因为如此，最终的设计是在效率和重量之间折衷。发动机在更高的涡轮进口温度下工作，在热力学上效率会更高，具有更高的功率重量比。内外涵发动机具有较好的推进效率，因而对于给定的推力来说，它可以用较小的涡轮。
4. The mean blade speed of a turbine has consid-operating at higher turbine inlet temperatures are erable effect on the maximum efficiency possible for thermally more efficient and have an improved power 5．慨括地讲，导向器叶片和涡轮工作叶片通道的设计主要依据空气动力学的考虑。从获得最佳效率，与压气机和燃烧室兼容出发，导向器叶片和涡轮工作叶片属于基本叶型。
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