Control of clearance between aircraft rotor blades and a casing
AssigneeSafran Aircraft Engines
InventorsTangi Brusq, Florence Valérie Bon, Damien Bonneau, Antoine Van Noort, Guilhem Camille François Verron
Life of this patent
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Abstract
A device for controlling clearance between the tips of rotating blades of an aircraft turbomachine and a casing. An air circulation path allows air to be blown onto the casing in order to change its temperature. In addition, heating means heat the circulating air.
Claims9
A clearance control device for controlling clearance between tips of blades of a rotor of an aircraft turbomachine and an annular casing of a stator of the aircraft turbomachine, said clearance control device comprising a flow path for a flow of air between:
- an air intake adapted to enable air to be taken from a first zone of the aircraft turbomachine,
- an air blower adapted to enable air to be blown to said annular casing, at the location of a second zone of the aircraft turbomachine, in order to modify a temperature of said annular casing, and
- air heating means adapted to interfere with air circulating in said air flow path, to enable said air to be heated,
- wherein the air heating means comprise electrical resistors which are electrically connected in parallel and are arranged successively in said air flow path, one after the other.
An aircraft turbomachine comprising:
- a clearance control device for controlling clearance between tips of blades of a rotor of an aircraft turbomachine and an annular casing of a stator of the aircraft turbomachine, said clearance control device comprising a flow path for a flow of air between:
- an air intake adapted to enable air to be taken from a first zone of the aircraft turbomachine,
- an air blower adapted to enable air to be blown to said annular casing, at the location of a second zone of the aircraft turbomachine, in order to modify a temperature of said annular casing, and
- air heating means adapted to interfere with air circulating in said air flow path, to enable said air to be heated, wherein:
- the clearance control device further comprises a control box mounted on said annular casing, and
- the air heating means are arranged upstream of the control box with respect to a direction of flow of the airflow from the air intake to the air blower and/or are arranged in the control box.
A clearance control device for controlling clearance between tips of blades of a rotor of an aircraft turbomachine and an annular casing of a stator of the aircraft turbomachine, the clearance control device comprising a flow path for a flow of air between:
- an air intake adapted to enable air to be taken from a first zone of the aircraft turbomachine,
- an air blower adapted to enable air to be blown to said annular casing, at the location of a second zone of the aircraft turbomachine, in order to modify a temperature of said annular casing, and
- air heating means adapted to interfere with air circulating in said air flow path, to enable said air to be heated,
- the clearance control device further comprising an air regulating system which comprises at least one of a valve disposed on the airflow path and a bypass circuit branched on the airflow path, the bypass circuit being adapted to bypass said air heating means, so that a variable quantity of air is allowed to flow in the airflow path.
Dependencies are inferred from the claim text.