Definition
A type of gas turbine engine combustion chamber in which air and combustion gases flow in a straight line from the compressor outlet, through the combustor, and into the turbine inlet without significant change in direction. Straight-through combustors include both can (multiple-can) and annular designs, and they require a longer engine but offer lower pressure losses than reverse-flow designs.
Plain English
A burner section in a jet engine where the air goes in one end and the hot gases come straight out the other end, without doubling back on itself.
Context Anchor
Seen in turbine engine descriptions, especially when comparing combustion chamber layouts during powerplant study or maintenance.
Derivation
Straight-through describes the airflow path: it travels in a straight line through the combustor, as opposed to a reverse-flow combustor where the air turns around and flows backward before entering the turbine.
Why Pilots Care
The combustor type affects engine length, weight, and pressure losses. Straight-through designs are common in larger turbine engines because they handle high airflow efficiently, while reverse-flow designs are used where a shorter engine is needed.
Intuition Check
“Straight-through” does not mean the combustor is just an empty tube. It means the air’s overall path through the burning section does not reverse direction.
Example Sentence 1
Most large turbofan engines use a straight-through annular combustor because it minimizes pressure loss across the burner section.
Example Sentence 2
Technicians check the straight-through combustor for wear during engine inspections.