Fan blade fairing assembly for an aircraft propulsion system
AssigneeRtx Corporation
InventorBrian K. Holland
Life of this patent
Estimating the term…
Abstract
A fan blade fairing assembly for a gas turbine engine includes a fairing body, a replaceable component, and a bonding assembly. The fairing body includes an outer wall, a first sidewall, and a second sidewall. The outer wall extends between and connects the first sidewall and the second sidewall. The replaceable component is bonded onto the fairing body. The bonding assembly includes an electrically debonding adhesive, a first conductive member, and a second conductive member. The electrically debonding adhesive bonds the replaceable component onto the fairing body. The electrically debonding adhesive is disposed between the first conductive member and the second conductive member.
Claims20
A fan blade fairing assembly for a gas turbine engine, the fan blade fairing assembly comprising:
- a fairing body including an outer wall, a first sidewall, and a second sidewall, the outer wall extending between and connects the first sidewall and the second sidewall;
- a replaceable component bonded onto the fairing body;
- and
- a bonding assembly including an electrically debonding adhesive, a first conductive member, and a second conductive member, the electrically debonding adhesive bonding the replaceable component onto the fairing body, the bonding assembly the electrically debonding adhesive disposed between the first conductive member and the second conductive member.
A fan blade fairing assembly for a gas turbine engine, the fan blade fairing assembly comprising:
- a fairing body forming an outer wall, a first sidewall, a second sidewall, and a mounting assembly lug, the outer wall extending between and connects the first sidewall and the second sidewall, the mounting assembly lug disposed between the first sidewall and the second sidewall;
- a first seal bonded onto the first sidewall;
- a second seal bonded onto the second sidewall;
- and
- a bushing mounted within the mounting assembly lug;
- each of the first seal, the second seal, and the bushing bonded to the fairing body by a bonding assembly including an electrically debonding adhesive.
A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:
- a bladed fan rotor configured for rotation about an axis of the gas turbine engine, the bladed fan rotor including a hub, a plurality of fan blades, and a fan blade fairing assembly, the fan blade fairing assembly mounted on the hub between a pair of circumferentially adjacent fan blades of the plurality of fan blades, the fan blade fairing assembly including:
- a fairing body including an outer wall, a first sidewall, and a second sidewall, the outer wall extending between and connects the first sidewall and the second sidewall, the outer wall forming an inner radial air flow surface bounding an air flow passage between the pair of circumferentially adjacent fan blades;
- a replaceable component bonded onto the fairing body;
- and
- a bonding assembly bonding the replaceable component onto the fairing body, the bonding assembly including an electrically debonding adhesive.
Dependencies are inferred from the claim text.