Turbine engine comprising a device for braking the fan rotor

Patent metadata

Field	Value
Publication number	US-10001027-B2
Application number	US-201514876585-A
Country	US
Kind code	B2
Filing date	Oct 6, 2015
Priority date	Oct 7, 2014
Publication date	Jun 19, 2018
Grant date	Jun 19, 2018

Abstract

The invention relates to a turbine engine comprising a fixed structure ( 7 ), a fan ( 1 ) rotor ( 3 ), having an axis (XX) of rotation, and emergency braking means ( 12, 13 ) of the rotor ( 3 ), in particular in the event of the loss of a blade of the fan ( 1 ), characterized in that said emergency braking means ( 12, 13 ) comprise a first ( 18 ) and a second ( 22 ) member supported by the fixed structure ( 7 ), said members ( 18, 22 ) respectively being configured so as to interact frictionally with a first ( 20 ) element which is complementary to the rotor ( 3 ), by forming a stop of the rotor ( 3 ) towards the rear along the axis (XX), and a second ( 24 ) element which is complementary to the rotor ( 3 ), by forming a stop of the rotor ( 3 ) towards the front along the axis (XX), when the emergency braking means ( 12, 13 ) are active.

First claim

The invention claimed is:

1. A turbine engine comprising a fixed structure, a fan rotor, having an axis of rotation, and an emergency brake of the fan rotor, said emergency brake comprising a first element, and a second element, a first member and a second member supported by the fixed structure, said first and second members respectively being configured so as to interact frictionally with the first element which is complementary to the fan rotor, by forming a stop of the fan rotor facing towards a rear of the turbine engine along the axis of rotation, and the second element which is complementary to the fan rotor, by forming a stop of the fan rotor facing towards a front of the turbine engine along the axis of rotation when the emergency brake is active, wherein the turbine engine further comprises a releasing means which is configured to release said first member so said first member moves in translation relative to the fixed structure along the axis of rotation, in a direction opposite to that for which it forms a stop, when the emergency brake is activated.

2. The turbine engine according to claim 1 , wherein the first member is arranged in front of the second member along the axis of rotation.

3. The turbine engine according to claim 2 , comprising at least a first bearing, which is mounted between the fan rotor and a support part, said releasing means comprising a fixing means for fixing said support part to the fixed structure which are arranged so as to break in the event of the loss of a blade of the fan, so as to form a device for decoupling the fan rotor.

4. The turbine engine according to claim 3 , wherein said releasing means comprises a part which is rigidly connected to said first member and is connected to the fixed structure by the fixing means, and wherein a limiter limits the axial movement of said part when said fixing means is broken.

5. The turbine engine according to claim 4 , which is arranged in such a way that said fixing means blocks said part from rotating about the axis of rotation when said fixing means is broken.

6. The turbine engine according to claim 1 , further comprising a biasing means which is configured to bias said first member against the first element when said fixing means is broken.

7. The turbine engine according to claim 6 , wherein the biasing means comprises a spring between said support part of said first member and the fixed structure.

8. The turbine engine according to claim 6 , wherein only the first member is biased by said biasing means, the second member being mounted so as to be rigidly connected to the fixed structure.

9. The turbine engine according to claim 1 , having a normal operating configuration, in particular before the loss of a fan blade, wherein the emergency brake is inactive and is configured in such a way that the gap along the axis of rotation between the first member and first element is larger than the gap between the second member and second element.

10. The turbine engine according to claim 1 , wherein the fan rotor is centered and guided by at least a second bearing which is mounted between the fixed structure and the fan rotor, said second bearing being located between said first and second members.

11. The turbine engine according to claim 1 , wherein the fan rotor comprises a drive shaft which supports at least one of said first and second elements.

12. The turbine engine according to claim 1 , wherein in a first phase when the emergency brake is active, the first and a second members move apart from one another.

Assignees

• Snecma

Inventors

• Becoulet Julien Fabien Patrick
• Tan-Kim Alexandre Jean-Marie

Classifications

• F05D2240/24

  for turbines · CPC title

• F01D21/04 Primary

  responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D21/006 Primary

  Arrangements of brakes (brakes per se F16D) · CPC title

• F05D2220/30

  in turbines · CPC title