GAS TURBINE COMPONENT AND METHOD OF FORMING

• Main Authors: DIAO, Xiaoxue, THOMAS, Nicholas, LIN, Dechao, KOTTILINGAM, Srikanth Chandrudu
• Format: Patent
• Language: English; French; German
• Published: 22.03.2017
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MECHANICAL ENGINEERING; WEAPONS

Components (100) are disclosed which include a first component section (102) and a second component section (104) joined to form a hollow structure (106) defining a plenum (108) having an interior surface (110), wherein the component sections (102, 104) each include mating ridges (120, 122, 124, 126) joined together along the length (114) of the plenum (108), and a corrosion-resistant cladding layer (128) including a corrosion-resistant material (130) overlaying the interior surface (110) of the plenum (108). In one embodiment, the component (100) is a gas turbine combustor fuel manifold (604). A method of forming the components (100) includes applying corrosion-resistant segments (134, 136) including a corrosion-resistant material (130) to each of the surfaces (200, 300) of the component sections (102, 104), and joining the component sections (102, 104) to form the component (100), wherein joining the component sections (102, 104) includes fusing the corrosion-resistant segments (134, 136) into the corrosion-resistant cladding layer (128), and joining the mating ridges (120, 122, 124, 126) of the component sections (102, 104).