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Ice crystal protection for a gas turbine engine

A gas turbine and engine technology, applied in the field of ice crystal protection arrangement structure, can solve the problems of poor anti-icing ability, rotor blade weight, aerodynamic performance and efficiency unoptimized, etc.

Pending Publication Date: 2020-09-01
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In this regard, the rotor blades have an increased radius of curvature at the leading edge, but conventional design criteria applied to medium and large geared engines result in rotor blades that are not optimized for weight, aerodynamic performance, efficiency, or ice protection poor

Method used

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  • Ice crystal protection for a gas turbine engine
  • Ice crystal protection for a gas turbine engine
  • Ice crystal protection for a gas turbine engine

Examples

Experimental program
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Embodiment Construction

[0084] 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.

[0085] Low pressure compressor 14 and high pressure compressor 15 include a respective plurality of compressor stages, each stage including a rotor and a stator. figure 2 A first stage 42 and a second stage 44 of the low pressure compressor 14 are shown. The first stage 42 is arranged upstream of the second stage 44 . The first stage 42 includes a first rotor having a first row of rotor blades 50 and downstream therefrom a first stator having a first row...

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PUM

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Abstract

The present invention relates to ice crystal protection for a gas turbine engine, and relates to a gas turbine engine comprising: a fan mounted for rotation about a primary longitudinal axis; an engine core including a compressor, a combustor, and a turbine coupled to the compressor by a shaft; and a reduction gearbox, wherein the compressor comprises a plurality of stages, each stage comprising arespective rotor and stator, a first stage of the plurality of stages being arranged at the inlet and comprising a first rotor having a plurality of blades; each blade extends chordally from a leading edge to a trailing edge and from a root to a tip up to a span height H, wherein 0% of the span height corresponds to the root and 100% of the span height corresponds to the tip, wherein the ratio ofthe maximum leading edge radius of curvature of the first rotor blade to the minimum leading edge radius of curvature of the first rotor blade is comprised between 2.2 and 3.5.

Description

technical field [0001] The present disclosure relates generally to gas turbine engines, and more particularly to arrangements for ice crystal protection of gas turbine engines, and in particular to arrangements for ice crystal protection of compressors of gas turbine engines. Background technique [0002] Gas turbine engines are used to power aircraft, ships, electrical generators, and more. A gas turbine engine typically includes an air inlet, a fan, one or more compressors, a combustor, one or more turbines, and an exhaust nozzle in axial series from front to rear. Air entering the intake is accelerated by a fan to create two airflows: a first airflow (core engine airflow) that enters the compressor through the intake duct and a second airflow (bypass airflow) that passes through a bypass duct to provide thrust. Air entering the compressor is compressed, mixed with fuel, and then fed to the combustor where combustion of the air / fuel mixture occurs. The high temperature a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/32F04D29/38
CPCF04D29/324F04D29/321F04D29/325F05D2240/303F01D5/141F05D2220/3218F01D25/02Y02T50/60F01D5/147F05D2220/32F05D2240/307
Inventor I.J.布斯菲尔德D.A.麦克杜格尔
Owner ROLLS ROYCE PLC