Interface device between two turbomachine elements
View Patent ↗An interface device between first and second turbomachine elements is provided. The interface device includes an annular air inlet structure including opposite first and second parts, designed to come into contact with the first and second turbomachine elements respectively, in which the first part is configured to be in swivel contact with the first element; and an elastic return device that can be placed around the air inlet structure and designed to come into contact with at least the first turbomachine element.
1. An interface device between first and second turbomachine elements, comprising:
an annular air inlet structure comprising opposite first and second parts, designed to come into contact with first and second turbomachine elements respectively, the first part being configured to be in swivel contact with the first element; and
an elastic return device, that can be placed around the air inlet structure and that will come into contact with at least the first element of the turbomachine.
2. The device according to claim 1 , wherein the air inlet structure comprises a fan flow seal ring for calibration of the airflow entering into the air inlet structure.
3. The device according to claim 2 , further comprising an elastic ring located between the fan flow seal ring and the second part of the air inlet structure.
4. The device according to claim 1 , wherein the second part of the air inlet structure comprises a plane surface in order to provide a sliding contact with the second turbomachine element.
5. The device according to claim 1 , wherein the first part of the air inlet structure comprises a swivel annular portion, an outside of the swivel annular portion in contact with an inner annular surface of the first turbomachine element.
6. The device according to claim 5 , wherein the elastic return device may be placed around the air inlet structure bearing on an outer annular surface of the first turbomachine element, opposite the inner annular surface of the first turbomachine element, such that at least part of the first turbomachine element comprising the inner and outer opposite annular surfaces is located between the elastic return device and the swivel annular portion of the air inlet structure.
7. A turbomachine comprising an interface device according to claim 1 , located between first and second turbomachine elements.
8. The turbomachine according to claim 7 , wherein the first turbomachine element is an active or inactive system (LPTACC or LPTCC) to control the clearance of the low pressure turbine of the turbomachine, and wherein the second turbomachine element is a scoop located on a part forming an envelope an outside of the part defines an inner delimitation surface of an annular fan flowpath of the turbomachine.
9. The turbomachine according to claim 7 , wherein the first turbomachine element comprises at least one retaining means of the air inlet structure configured to prevent the air inlet structure from separating from the first turbomachine element.
10. The turbomachine according to claim 9 , wherein said at least one retaining means comprises a projecting rib designed to cooperate with the air inlet structure.
11. An interface device between first and second turbomachine elements, comprising:
an annular air inlet structure comprising opposite first and second parts, designed to come into contact with first and second turbomachine elements respectively, the first part being configured to be in swivel contact with the first element; and
an elastic return device, that can be placed around the air inlet structure and that will come into contact with at least the first element of the turbomachine,
wherein the second part of the air inlet structure comprises a plane surface in order to provide a sliding contact with the second turbomachine element.