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US 9,435,215 B2Granted
Gas turbine structure
AssigneeGKN Aerospace Sweden AB
InventorsNiklas Jansson, Robert Reimers
Life of this patent
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AssigneeGKN Aerospace Sweden AB
InventorsNiklas Jansson, Robert Reimers
Estimating the term…
A gas turbine structure includes a guide vane. The gas turbine structure (further includes a first housing and a second housing and the guide vane extends from the first housing to the second housing. The guide vane includes a leading edge and a trailing edge and the guide vane extends from the leading edge to the trailing edge along a mean camber line. The guide vane includes a first attachment structure, a first fastening arrangement and a second fastening arrangement. Moreover, the first attachment structure includes a stiffening member extending over at least a portion of a circumference of the first housing. Furthermore, the stiffening member includes a stiffening member center point as measured along the mean camber line.
A gas turbine structure comprising a guide vane, the gas turbine structure further comprising a first housing and a second housing and the guide vane extending from the first housing to the second housing, the guide vane comprising a leading edged and a trailing edge, the guide vane extending from the leading edge to the trailing edge along a mean camber line, the guide vane comprising a first attachment structure, a first fastening means and a second fastening means, the first attachment structure comprising a stiffening member extending over at least a portion of a circumference of the first housing, the stiffening member comprising a stiffening member centre point as measured along the mean camber line, the first attachment structure being adapted to be releasably attached to the guide vane by the first and second fastening means such that the first fastening means is located at a first fastening position along the mean camber line and the second fastening means is located at a second fastening position along the mean camber line, the attachment structure being attached to the first housing the first and second fastening positions are located on separate sides of the stiffening member centre point along the mean camber line.
A gas turbine engine comprising a gas turbine structure according to any one of the preceding claims.
A gas turbine structure comprising a guide vane, the gas turbine structure further comprising a first housing and a second housing and the guide vane extending from the first housing to the second housing, the guide vane comprising a leading edge and a trailing edge, the guide vane extending from the leading edge to the trailing edge along a mean camber line, the guide vane comprising a first attachment structure, a first fastener and a second fastener, the first attachment structure comprising a stiffener extending over at least a portion of a circumference of the first housing, the stiffener comprising a stiffener centre point as measured along the mean camber line, the first attachment structure being adapted to be releasably attached to the guide vane by the first and second fastener such that the first fastener is located at a first fastening position along the mean camber line and the second fastener is located at second fastening position along the mean camber line, the attachment structure being attached to the first housing wherein the first and second fastening positions are located on separate sides of the stiffener centre point along the mean camber line.
Dependencies are inferred from the claim text.