Unducted propeller gas turbine comprising a cooling air channel and a variable bleed valve ejection channel
AssigneesSafran Aircraft Engines, General Electric Company
InventorTom Everaets
Life of this patent
Estimating the term…
Abstract
A gas turbine includes two unducted propellers, a main channel, a compression stage located in the main channel, the main channel supplying the compression stage with air, a cooling channel extending from a cooling inlet opening into the main channel, the cooling inlet being located upstream of the compression stage with reference to a direction of flow of the air through the gas turbine, a heat exchanger located in the cooling channel, an ejection channel opening into the main channel and into the cooling channel so that air passing through the ejection channel ventilates the heat exchanger, and a variable bleed valve that adjust an air flow rate in the ejection channel.
Claims14
A method for controlling a gas turbine, the method comprising:
- supplying air into a main channel through a main inlet, the main inlet being located between two unducted propellers of the gas turbine,
- producing compressed air by flowing the air supplied through a compression stage located in the main channel,
- producing a complementary airflow through an ejection channel, the ejection channel opening into the main channel and into a cooling channel, so that air passing through the ejection channel ventilates ana heat exchanger located in the cooling channel, the cooling channel extending from a cooling inlet, the cooling inlet opening into the main channel, the cooling inlet being located upstream of the compression stage with reference to a direction of flow of the air through the gas turbine,
- comparing a rotational speed of one of the unducted propellers with a first predetermined speed, and
- if the rotational speed exceeds the first predetermined speed, setting to zero a flow of the complementary airflow.
A gas turbine comprising:
- two unducted propellers,
- a main channel comprising a main inlet, the main inlet being located between the two unducted propellers,
- a compression stage located in the main channel, the main channel being configured to supply the compression stage with air,
- a cooling channel extending from a cooling inlet opening into the main channel, the cooling inlet being located upstream of the compression stage with reference to a direction of flow of the air through the gas turbine,
- a heat exchanger located in the cooling channel,
- an ejection channel opening into the main channel and into the cooling channel so that air passing through the ejection channel ventilates the heat exchanger, and
- a variable bleed valve configured to adjust an air flow rate in the ejection channel.
Dependencies are inferred from the claim text.