Turbofan comprising a low-supercritical-pressure shaft

Patent metadata

Field	Value
Publication number	US-11047338-B2
Application number	US-201716085086-A
Country	US
Kind code	B2
Filing date	Mar 15, 2017
Priority date	Mar 15, 2016
Publication date	Jun 29, 2021
Grant date	Jun 29, 2021

Abstract

A turbofan engine including: a turbine shaft; a fan shaft; and a reduction mechanism coupling the turbine shaft and the fan shaft, is provided. The turbofan engine has a bypass ratio greater than or equal to 10, and the turbine shaft is supported by four bearings such that the flexural deformation modes of the turbine shaft are positioned in transient phase or outside the operating range of the turbofan engine.

First claim

The invention claimed is:

1. A bypass turbofan engine comprising:
a turbine shaft,
a fan shaft, and
a reduction mechanism, coupling the turbine shaft and the fan shaft,
wherein the turbofan engine has a bypass ratio greater than or equal to 10,
wherein the turbine shaft is supported by four bearings such that flexural deformation modes of the turbine shaft are positioned in transient phase or outside an operating range of the turbofan engine,
wherein the turbofan engine further comprises, from upstream to downstream in a direction of flow of gases in the turbofan engine:
a fan driven by the fan shaft,
a low-pressure compressor driven by the turbine shaft,
a high-pressure compressor, and
a turbine, which drives in rotation the turbine shaft,

wherein the turbofan engine further comprises an inter-compressor housing extending between the low-pressure compressor and the high-pressure compressor,
wherein a first of the four bearings which supports the turbine shaft is mounted on the inter-compressor housing,
wherein the turbofan engine further comprises a casing extending between the reduction mechanism and the low-pressure compressor,
wherein a second of the four bearings which supports the turbine shaft is mounted on the casing,
wherein the turbofan engine further comprises a discharge casing extending downstream from the turbine, and
wherein a third of the four bearings is directly mounted on the discharge casino.

2. The turbofan engine according to claim 1 , wherein the first of the four bearings comprises a flexible cage, whereas the second of the four bearings is devoid of a flexible cage.

3. The turbofan engine according to claim 1 , wherein the turbine comprises, from upstream to downstream, a high-pressure turbine and a low-pressure turbine separated by an inter-turbine casing, a fourth of the four bearings being mounted on the inter-turbine casing, upstream from the third of the fourth bearings.

4. The turbofan engine according to claim 3 , wherein the fourth of the four bearings comprises a flexible cage and, whereas the third of the four bearings is devoid of a flexible cage.

5. The turbofan engine according to claim 3 , wherein the fourth of the four bearings further comprises an oil film damper.

6. The turbofan engine according to claim 1 , wherein the high-pressure compressor is driven by a high-pressure shaft, said high-pressure shaft being mounted on a front bearing and a rear bearing, wherein the front bearing extends downstream from the first of the four bearings.

7. The turbofan engine according to claim 1 , wherein the high-pressure compressor comprises at least eight rotor stages.

8. The turbofan engine according to claim 7 , wherein an overall compression ratio of the low-pressure compressor and of the high-pressure compressor is greater than or equal to 30.

9. The turbofan engine according to claim 7 , wherein an overall compression ratio of the low-pressure compressor and of the high-pressure compressor is greater than or equal to 40.

10. The turbofan engine according to claim 1 , wherein a bypass ratio of the turbofan engine is between 12 and 18.

11. The turbofan engine according to claim 1 , wherein a reduction ratio of the reduction mechanism is between 2.5 and 5.

12. The turbofan engine according claim 1 , wherein an absolute maximal speed encountered by the turbine shaft is between 8000 revolutions per minute and 12 000 revolutions per minute.

13. The turbofan engine according to claim 1 , wherein the high-pressure compressor comprises between eight and twelve rotor stages.

14. The turbofan engine according to claim 1 , wherein an absolute maximal speed encountered by the turbine shaft is around 10 000 revolutions per minute.

15. The turbofan engine according to claim 1 , wherein the first of the four bearings further comprises an oil film damper.

Assignees

• Safran Aircraft Engines

Inventors

• Dievart Jeremy
• Benslama Yanis
• Nowakowski Nathalie

Classifications

• F05D2220/326

  to drive shrouded, low solidity propeller · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2220/327

  to drive shrouded, high solidity propeller · CPC title

• F02K3/06 Primary

  with front fan · CPC title