Abstract: A method for delivering fuel to a combustor of a gas turbine engine includes: injecting fuel into a conduit of a fuel manifold; directing the fuel through a continuous first portion of the conduit; directing the fluid from the first portion into an inflexion of the conduit being a single exit of the first portion; directing the fuel from the inflexion into a second portion of the conduit in serial flow communication with the first portion; and carrying the fuel in the second portion in a direction different from that of the fuel in the first portion. As the fuel flows through the second portion of the conduit, the fuel exits from the second portion of the conduit into a plurality of fuel injection nozzles in exclusive fluid flow communication with the second portion for ejection into a combustor of the gas turbine engine.

Abstract: A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.

Abstract: A method for delivering fuel to a combustor of a gas turbine engine includes: injecting fuel into a conduit of a fuel manifold; directing the fuel through a continuous first portion of the conduit; directing the fluid from the first portion into an inflexion of the conduit being a single exit of the first portion; directing the fuel from the inflexion into a second portion of the conduit in serial flow communication with the first portion; and carrying the fuel in the second portion in a direction different from that of the fuel in the first portion. As the fuel flows through the second portion of the conduit, the fuel exits from the second portion of the conduit into a plurality of fuel injection nozzles in exclusive fluid flow communication with the second portion for ejection into a combustor of the gas turbine engine.

Abstract: The described gas turbine engine fuel manifold includes one or more fuel conduits defined within a ring-shaped manifold body, each of the fuel conduits being fluidly connected to a respective separate group of fuel injection nozzles. Each of the fuel conduits, which extend from a conduit inlet to a conduit end, include a first portion extending continuously between the conduit inlet and an inflexion of the conduit, and a second portion downstream of the first portion and connected thereto in serial flow communication, the second portion extending between the inflexion and the conduit end. The inflexion being a single exit of the first portion such that fuel flows uninterrupted between the conduit inlet and the inflexion. The respective separate group of fuel injection nozzles of the fuel conduit fluidly communicating exclusively with the second portion of the fuel conduit.

Abstract: A method for delivering fuel from a fuel nozzle of a combustor of a gas turbine engine includes directing fuel from a fuel source through a flow splitter to provide at least two concentric fuel flows, filming the concentric two fuel flows on concentrically arranged inwardly facing filming surfaces that are disposed downstream of the flow splitter, and atomizing the concentric fuel flows into a core air flow.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has opposed front and back faces, the back face facing the inner surface of the combustor shell and being spaced therefrom to define an air gap. The front and back faces have a perimeter including opposed lateral edges extending between opposed circumferentially extending edges. The lateral edges of adjacent heat shield panels have complementary non-linear profiles defining an asymmetric heat shield panel interface.

Abstract: The described gas turbine engine fuel manifold includes one or more fuel conduits defined within a ring-shaped manifold body, each of the fuel conduits being fluidly connected to a respective separate group of fuel injection nozzles. Each of the fuel conduits, which extend from a conduit inlet to a conduit end, include a first portion extending continuously between the conduit inlet and an inflexion of the conduit, and a second portion downstream of the first portion and connected thereto in serial flow communication, the second portion extending between the inflexion and the conduit end. The inflexion being a single exit of the first portion such that fuel flows uninterrupted between the conduit inlet and the inflexion. The respective separate group of fuel injection nozzles of the fuel conduit fluidly communicating exclusively with the second portion of the fuel conduit.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has a sealing rail extending from a back side thereof and a plurality of bolted connections securely holding the heat shield panel on the combustor shell with the sealing rail in sealing contact with the inner surface of the combustor shell. Each pair of adjacent heat shield panels comprises first and second panels having adjoining lateral edges, the first panel having a boltless area on its back side at a location adjacent to its adjoining lateral edge. The second panel has a first one of its bolted connections provided adjacent to its adjoining lateral edge and in facing relationship with the boltless area of the first panel.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has opposed front and back faces, the back face facing the inner surface of the combustor shell and being spaced therefrom to define an air gap. The front and back faces have a perimeter including opposed lateral edges extending between opposed circumferentially extending edges. The lateral edges of adjacent heat shield panels have complementary non-linear profiles defining an asymmetric heat shield panel interface.

Abstract: A combustor heat shield assembly comprises a circumferential array of heat shield panels individually mounted to an inner surface of a combustor shell. Each heat shield panel has a sealing rail extending from a back side thereof and a plurality of bolted connections securely holding the heat shield panel on the combustor shell with the sealing rail in sealing contact with the inner surface of the combustor shell. Each pair of adjacent heat shield panels comprises first and second panels having adjoining lateral edges, the first panel having a boltless area on its back side at a location adjacent to its adjoining lateral edge. The second panel has a first one of its bolted connections provided adjacent to its adjoining lateral edge and in facing relationship with the boltless area of the first panel.

Abstract: A method and device for improved pressure balancing in a bearing chamber pressurization system for gas turbine engines employ a partition member to substantially separate first and second air-oil seals of the bearing housing.