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Aircraft engine

An aircraft and engine technology, applied in the direction of machine/engine, gear transmission, air transportation, etc., to achieve the effect of power density and small rotor diameter

Pending Publication Date: 2021-06-08
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, when manufacturing engines with larger fan diameters, the present inventors have discovered that simply enlarging components of known engine types may not result in an efficient design
For example, there may be issues associated with fitting the gearbox and fan shaft inside the engine

Method used

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Embodiment approach

[0537] In various embodiments, the ratio of radial flexural stiffness to moment of inertia may be defined as:

[0538]

[0539] In various embodiments, the ratio of radial bending stiffness to moment of inertia may be greater than or equal to 2.5×10 -2 Nkg -1 m -3 (ie, (N / m) / (kg.m 2 )), and optionally greater than or equal to 0.05 Nkg -1 m -3 .

[0540] In some embodiments, such as those in which the fan diameter is in the range of 240 cm to 280 cm, the ratio of radial bending stiffness to moment of inertia may be greater than or equal to 0.05 Nkg -1 m -3 . In some embodiments, such as those in which the fan diameter is in the range of 330 cm to 380 cm, the ratio of radial bending stiffness to moment of inertia may be greater than or equal to 0.025 Nkg -1 m -3 .

[0541] In various embodiments, the ratio of radial flexural stiffness to moment of inertia may be between 2.5x10 -2 Nkg -1 m -3 to 6.0Nkg -1 m -3 range, and optionally within 0.05Nkg -1 m -3 to 3....

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Abstract

A gas turbine engine (10) for an aircraft comprising: an engine core (11) comprising a turbine (19), a compressor (14), and a core shaft (26) connecting the turbine to the compressor; a fan (23) located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox (30) that receives an input from the core shaft (26) and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, the gearbox (30) being an epicyclic gearbox (30) comprising a sun gear (28), a plurality of planet gears (32), a ring gear (38), and a planet carrier (34) arranged to have the plurality of planet gears (32) mounted thereon; and a gearbox support (40) arranged to at least partially support the gearbox within the engine. A flight cycle ratio of: the torsional shear stress of the gearbox support 40 at maximum takeoff conditions the torsional shear stress of the gearbox support 40 at cruise conditions is in the range of from is less than or equal to 3.20. A method (2000) of operating the gas turbine engine is also disclosed.

Description

technical field [0001] The present disclosure relates to gas turbine engines, and in particular, to gas turbine engines for aircraft. Aspects of the present disclosure also relate to aircraft including the gas turbine engine and methods of operating the gas turbine engine. Background technique [0002] Gas turbine engines used for aircraft propulsion have many design factors that affect overall efficiency and power output or thrust. A general purpose of gas turbine engines is to provide low specific fuel consumption (SFC). To enable higher thrust with high efficiency, larger diameter fans can be used. To facilitate the use of larger fan sizes, a gearbox is provided having an output to the fan shaft via which the fan is driven. The gearbox receives drive from the spindle connected to the turbine system at the core of the engine. The gearbox allows the fan to be operated at a reduced rotational speed than would be the case with a direct drive. [0003] However, when manuf...

Claims

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Application Information

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IPC IPC(8): F16H1/32F16H48/10F16H57/08F16H57/025F02C7/36F02C3/04F02K3/06B64D27/10
CPCB64D27/10F02C3/04F02C7/36F02K3/06F16H1/32F16H48/10F16H57/025F16H57/08F02C7/20F05D2260/40311F05D2260/941Y02T50/60F02C3/113F16H1/2809F16H57/082
Inventor 马克·斯普鲁斯
Owner ROLLS ROYCE PLC