Chapter 4
LYCOMING T53
4.1.
INTRODUCTION
The two sections of this chapter discuss, in detail, the
Lycoming T53 series gas turbine engine used in Army aircraft.
Section I gives a general description of the T53, describes the
engine's five sections, explains engine operation, compares models
and specifications, and describes the engine's airflow path. The
second section covers major engine assemblies and systems.
Basically, all models of the T53 engine are of the same
design. The major difference on models later than the T53L11 is
that they have two gas producer turbines (N1) and two freepower
turbines (N2) instead of the single stage turbine used on the L 11
and earlier models. The engine models described in this chapter are
primarily the T53L13, and T53L701. However, the description and
information given is applicable to all models except where noted.
Section I. Operational Description of the T53 Gas Turbine Engine
4.2.
GENERAL
The information in this section is important to you because it
describes the engine's airflow path through the inlet, compressor,
diffuser, combustion, and exhaust sections, and explains the
operational relationship of these sections. In addition differences
between models and specifications are compared. Except for the
paragraph comparing models, this section's coverage is limited to the
T53L13 and 701.
4.3.
The T53 series gas turbine engine is an annular reverseflow,
freepower turbine powerplant developed for fixed and rotarywing
aircraft. As shown in figure 4.1, the engine consists of inlet,
compressor, diffuser, combustion, and exhaust sections. All these
are designed to include an annular or circular flow path for the air
or hot gases, and they are structurally dependent on one another.
These sections support all internal rotating systems and have
attaching capabilities for engine accessories.
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