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Gas turbine engine having core mount

A technology for gas turbines and mounting parts, applied to the components of pumping devices for elastic fluids, pump components, engine components, etc., which can solve the problems of increased bending load of the engine core

Pending Publication Date: 2020-11-03
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] For example, the skilled artisan will appreciate that if the fan size of a gas turbine engine is increased, the bending loads on the engine core may detrimentally increase

Method used

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  • Gas turbine engine having core mount
  • Gas turbine engine having core mount
  • Gas turbine engine having core mount

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0375] figure 1 A gas turbine engine 10 with a main axis of rotation 9 is shown. The engine 10 includes an air intake 12 and a propeller fan 23 that generates two airflows: a core airflow A and a bypass airflow B. The gas turbine engine 10 includes a core 11 receiving a core flow A. As shown in FIG. The engine core 11 includes a low-pressure compressor 14 , a high-pressure compressor 15 , a combustion device 16 , a high-pressure turbine 17 , a low-pressure turbine 19 and a core exhaust nozzle 20 in series in axial flow. A nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass exhaust nozzle 18 . The bypass gas flow B flows through the bypass duct 22 . The fan 23 is attached to and driven by the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30 .

[0376] In use, the core gas stream A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 for further compression. T...

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PUM

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Abstract

The invention relates to a gas turbine engine with a core mount. The present disclosure relates to a gas turbine engine (10) for an aircraft, the gas turbine engine comprising: an engine core (11) comprising a first lower pressure compressor (14) and a second higher pressure compressor (15); and an outer core housing (76) surrounding the compressor system. The outer core housing comprises a firstflange connection (60) arranged to allow separation of the outer core housing (76) at an axial position of the first flange connection (60), the first flange connection (60) having a first flange radius (104), wherein the first flange connection (60) is a first flange connection downstream of the axial position.

Description

technical field [0001] The present disclosure relates to gas turbine engines for aircraft, and more particularly, to gas turbine engines with specified relative component locations. Background technique [0002] Those skilled in the art will understand that simply scaling up an engine may introduce problems such as increased stress, strain and / or bending moments on engine parts and / or on the wing of the aircraft to which it is mounted. Therefore, it may be appropriate to reconsider the engine parameters. [0003] For example, skilled artisans will understand that if the fan size of a gas turbine engine is increased, the bending loads on the engine core may be detrimentally increased. Accordingly, it may be appropriate to redesign the engine core and / or support components of the gas turbine engine. Contents of the invention [0004] According to a first aspect there is provided a gas turbine engine for an aircraft, the gas turbine engine comprising an engine core comprisi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/06F02C7/20F02C3/113F04D29/32F04D29/38F04D29/54
CPCF02K3/06F02C7/20F02C3/113F04D29/325F04D29/388F04D29/542F01D25/243F05D2240/14F01D25/246Y02T50/60F01D15/12F05D2220/323F05D2240/90
Inventor C.K.坎南加拉J.C.加斯克尔S.T.索恩顿T.菲尔普
Owner ROLLS ROYCE PLC