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ROTOR SPINNER OR FAIRING APPARATUS

IP.com Disclosure Number: IPCOM000249712D
Publication Date: 2017-Mar-24
Document File: 8 page(s) / 203K

Publishing Venue

The IP.com Prior Art Database

Abstract

A fairing assembly including a spinner or similar fairing and a supporting component are provided for a machine such as a gas turbine engine. A joint configuration between the two components is provided which minimizes exposed drag-causing elements.

This text was extracted from a PDF file.
This is the abbreviated version, containing approximately 35% of the total text.

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ROTOR SPINNER OR FAIRING APPARATUS

ABSTRACT

[0001] A fairing assembly including a spinner or similar fairing and a supporting

component are provided for a machine such as a gas turbine engine. A joint configuration

between the two components is provided which minimizes exposed drag-causing

elements.

BACKGROUND

[0002] A gas turbine engine includes a turbomachinery core having a high pressure

compressor, combustor, and high pressure turbine in serial flow relationship. The core is

operable in a known manner to generate a primary flow of propulsive gas. A typical

turbofan engine adds a low pressure rotor including a low pressure turbine driven by the

core exhaust gases, which in turn drives a fan through a shaft to generate a bypass flow of

propulsive gas. In the case of a high bypass engine this provides the majority of the total

engine thrust.

[0003] The fan includes an array of fan blades extending radially outward from a fan

disk. Typically an aerodynamic fairing referred to as a spinner assembly is provided at

the forward end of the fan disk to reduce drag and smooth airflow into the fan blades.

[0004] Typically the spinner assembly includes a spinner connected to mounting

structure referred to as an "aft support ring". Some existing spinner assemblies utilize a

bolted connection between the two components. The spinner assembly can also be used

for balancing the low pressure rotor, by providing holes in the spinner to accept trim

bolts.

[0005] One problem with prior art spinner assemblies is that the numerous bolts used

for assembly and balancing are exposed to the exterior flowpath and can cause drag and

disruption to the desired airflow pattern.

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[0006] Described herein is a spinner configured to reduce aerodynamic losses and ease

assembly.

BRIEF DESCRIPTION OF THE DRAWINGS

[0007] The concept may be best understood by reference to the following description

taken in conjunction with the accompanying drawing figures in which:

[0008] FIG. 1 is a schematic half-sectional view of a portion of a fan rotor of a gas

turbine engine;

[0009] FIG. 2 is a schematic exploded view of a spinner assembly shown in FIG. 1;

[0010] FIG. 3 is a view taken along lines 3-3 of FIG 2;

[0011] FIG. 4 is a view taken along lines 4-4 of FIG. 2; and

[0012] FIG. 5 is a cross-sectional view of a portion of a bolted joint of the spinner

assembly.

DETAILED DESCRIPTION OF THE CONCEPT

[0013] Referring to the drawings wherein identical reference numerals denote the

same elements throughout the various views, FIG. 1 depicts a fan rotor 10 which forms a

part of a high-bypass gas turbine engine. It will be understood that the principles

described herein are equally applicable to other types of turbine engines, as well as to

other types of rotors (e.g. propellers) having blades or blade-like components mounted

thereto. It should be further appreciated that the principles described herein may be

extended to any type of machinery fairing (rotating or static) which connec...