In general, techniques are described for emulating mobile authentication methods to establish authenticated connectivity between a mobile service provider gateway and a wireless device attached to an alternate access network. For example, a system operating according to the described techniques includes a mobile service provider network, an alternate access network having an access gateway, and an authentication server of the mobile service provider network that receives a network access request. A subscriber database responds to the network access request with virtual mobility information, wherein the network access request does not include an International Mobile Subscriber Identity (IMSI), and wherein the virtual mobility information comprises a virtual IMSI. The access gateway uses the virtual mobility information to signal a mobile network gateway of the mobile service provider network to establish a service session for the wireless device over the alternate access network that is anchored by the mobile network gateway.

Non-mobile authentication for mobile network gateway connectivity

The thrust reverser comprises a first reverser door and a second reverser door asymmetrically pivotable between a stowed position and a deployed position, one having a pivot axis closer to the central axis than the other.

Thrust reverser nozzle for a turbofan gas turbine engine

The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm.

Thrust Reverser for a Turbofan Gas Turbine Engine

A thrust reverser assembly for use in a turbofan engine assembly. The engine assembly includes a core gas turbine engine and a core cowl which circumscribes the core gas turbine engine. A nacelle is positioned radially outward from the core cowl to define a fan nozzle duct between the core cowl and a portion of the nacelle. The nacelle includes a stationary cowl. The thrust reverser assembly includes a first translating cowl that is slidably coupled to the nacelle. The first translating cowl is positionable with respect to the stationary cowl. A second translating cowl is slidably coupled to the nacelle such that the first translating cowl is positioned between the stationary cowl and the second translating cowl. The second translating cowl is positionable with respect to the first translating cowl. A positioning assembly is coupled to the first translating cowl. An actuator assembly is operatively coupled to the second translating cowl for selectively moving the second translating cowl. The actuator assembly is configured to engage the positioning assembly to selectively move the first translating cowl.

System and method for operating a thrust reverser for a turbofan propulsion system

A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed.

Pivoting door thrust reverser for a turbofan gas turbine engine

The thrust reverser is used with a gas turbine engine and includes first (24) and second (26) doors pivotable between a stowed position and a deployed position. When deployed, pivoting fairings (36) on the first door are moved so as to give room to the second door as its trailing edge moves within the first door. When stowed, the second door (26) preferably provides the locking mechanism to the pivoting fairings (36) of the first door (24).

Pivoting Fairings for a Thrust Reverser

A thrust reverser nozzle (22) for an engine nacelle (20) includes opposite and asymmetrically pivoting first and second doors (24,26) defining a nacelle aft section (20a), first and second trailing edges (24a, 26a) of the first and second doors (24,26) adjacent to an outlet (28) of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge (24a) is positioned behind the second trailing edge (26a) when the doors are in the deployed position, and the first and second fairings (34,36) attached to the first and second doors in relative fixed positions to the first and second doors respectively Male contour middle portions (38) of the first fairings (34) may complementarily match female contour middle portions (40) of the second fairings (36) and are received within the female contour middle portion when the doors are in the stowed position.

Jean-Pierre Lair

Papers

Thrust reverser nozzle for a turbofan gas turbine engine

Thrust Reverser for a Turbofan Gas Turbine Engine

Pivoting door thrust reverser for a turbofan gas turbine engine

Pivoting Fairings for a Thrust Reverser

Nested fairing thrust reverser