Abstract: A protective sheath for a fluid-carrying tube is made from a larger tube cut into longitudinal tube segments and slice into opposed halves before being re-secured together about the fluid-carrying tube. Slip joints are preferably provided between adjoining outer tube segments.

Abstract: A combustor heat shield comprises a heat shield member defining at least one opening for receiving a fuel nozzle. A louver is received in the opening. The louver has a flow diverting portion extending radially outwardly from the opening for directing air along the hot side of the heat shield member.

Abstract: A combustor for a gas turbine engine having an inner combustor wall and an outer combustor wall with a number of heat shields mounted internally thereto with fasteners. Each combustor wall has an end wall defining a combustor dome with a number of: fuel nozzle openings; impingement air openings; and heat shield fastener openings. Each of the end walls has an overlapping portion with mutually engaging sealing surfaces with the openings within the overlapping portions being aligned in overlapping pairs, where an exterior overlapping portion has at least one of the aligned openings of one overlapping pair being of larger dimension than the aligned opening in an interior overlapping portion.

Abstract: A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield.

Abstract: A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions.

Abstract: A gas turbine engine combustor includes a liner having a dome portion with a plurality of openings defined therein for receiving fuel nozzles and a plurality of holes defined around each opening. The holes directing air into the combustion chamber in a spiral pattern around an axis along which fuel is injected into the combustor by the fuel nozzles.

Abstract: An assembly for sealingly mounting a device in a hole in a pressure vessel casing, the assembly transferring a load produced by pressurized fluid to the casing and retaining the stem to the casing.

Abstract: The support boss is used in a combustor of a gas turbine engine. It comprises a side wall defining an internal space. The side wall has at least one air inlet orifice. It also comprises a bottom wall closing one end of the internal space. The bottom wall has at least one air outlet orifice.

Abstract: A protective sheath for a fluid-carrying tube is made from a larger tube cut into longitudinal tube segments and slice into opposed halves before being re-secured together about the fluid-carrying tube. Slip joints are preferably provided between adjoining outer tube segments.

Abstract: A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions.

Abstract: A heat shield for a gas turbine engine combustor includes an apparatus for providing a spiral flow to improve at least the cooling of the heat shield.

Abstract: A head part of an annular combustor for a gas turbine includes an annular bulkhead at the upstream end of the combustor. The bulkhead includes a first annular section integrally, inwardly and radially extending from the outer annular wall of the combustor, and a second annular section integrally, outwardly and radially extending from the annular inner wall of the combustor. The first and second annular sections are overlapped adjacent to the annular inner wall and secured together by segmented heat shields which have integrated threaded studs engaging with self-locking nuts, and cover the downstream side of bulkhead. The first annular section has a plurality of apertures circumferentially spaced apart from one another to receive fuel burners. Each burner is radial-displaceably positioned in the aperture and sealed by a burner collar, which is clamped between the heat shield and the bulkhead wall.

Abstract: A head part of an annular combustor for a gas turbine engine according to the present invention includes an annular bulkhead at the upstream end of the combustor. The bulkhead includes a first annular section integrally, inwardly and radially extending from the outer annular wall of the combustor, and a second annular section integrally, outwardly and radially extending from the annular inner wall of the combustor. The first and second annular sections are overlapped adjacent to the annular inner wall and secured together by segmented heat shields which have integrated threaded studs engaging with self-locking nuts, and cover the downstream side of bulkhead. The first annular section has a plurality of apertures circumferentially space apart from one another to receive fuel burners therein, respectively. Each burner is radial-displaceably positioned in the aperture and sealed by a burner collar. The burner collar is clamped between the heat shield and the bulkhead wall.

Abstract: The invention relates to a radial split diffuser with an inner casing and an outer casing joined together along a cylindrical joint. Each diffuser passage is intersected by and extends transversely across the joint. The advantages of this design include: the elimination of a transition within the initial portion of the passages where air flow speeds are supersonic and minute surface discontinuities can significantly effect performance; and the simplification of manufacturing through use of metal castings to replace sheet metal fabrications in the manufacture of diffusers. The joint in the present invention can be located downstream from the diffuser inlet a sufficient distance in a lower velocity area. The joint is located to enable access for precise machining of the critical initial portion of the passages within the inner casing, and to minimize air flow disturbance in the initial portion.