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Hybrid propeller hubcap bracket

A hybrid and hanger technology, which is applied in the fan area and the field of hybrid aircraft components, can solve the problem that the propeller hub cap support ring cannot be manufactured.

Active Publication Date: 2017-12-05
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to material limitations or properties, such propeller spinner support rings cannot be manufactured from a less dense single material such as aluminum

Method used

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  • Hybrid propeller hubcap bracket
  • Hybrid propeller hubcap bracket
  • Hybrid propeller hubcap bracket

Examples

Experimental program
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Embodiment Construction

[0022] Reference will now be made in detail to the provided embodiments, one or more examples of which are illustrated in the accompanying drawings. Each example is provided by way of illustration, not limitation of the disclosed embodiments. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present embodiment without departing from the scope or spirit of the disclosure. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield still a further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0023] refer to Figure 1-10 , showing various embodiments of hybrid propeller spinner support structures. More specifically, a hybrid propeller spinner bracket is provided such that a first portion of the bracket is formed from a first m...

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PUM

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Abstract

A hybrid support ring for a diverter of an aircraft engine, comprising a hanger defined by flanges and rearwardly extending struts having lugs, the hanger also extending circumferentially, the hanger being defined by a Formed from one material, the band extends circumferentially and is disposed in the lug, and the band is formed from a second material.

Description

technical field [0001] The disclosed embodiments generally relate to fan zones of aircraft engines. More particularly, but not by way of limitation, this embodiment relates to hybrid aircraft components formed from two or more parts of different composition. Background technique [0002] A typical gas turbine engine generally has a front end between which several cores or propulsion members of the gas turbine engine are axially positioned. An air inlet or intake is at the front end of the engine. Moving toward the rear, in that order, the intake follows the compressor, combustor, turbine, and nozzles at the rear of the engine. It will be readily apparent to those skilled in the art that additional components may also be included in the engine, such as low and high pressure compressors, and high and low pressure turbines. However, this is not an exhaustive list. The engine also typically has an internal shaft arranged along the central longitudinal axis of the engine. Th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/06F01D25/24F02C7/04F04D29/32
CPCF01D5/066F01D25/243F02C7/04F05D2220/36F05D2300/121F05D2300/603F04D29/023F04D29/321F05D2300/171F05D2300/133Y02T50/60B64C27/54
Inventor B.J.罗比M.J.比肖普
Owner GENERAL ELECTRIC CO