Patent ID: 9500087
Filing Date: 2016-11-22
CPC Classification: F01D,F05D,Y10T

Claim Text:
1. A turbine component, comprising: a hollow aerofoil and an impingement tube located within the hollow aerofoil, wherein the hollow aerofoil includes a cavity including opposed rear and fore portions defined by interior surfaces of respective trailing edge and leading edge regions of the hollow aerofoil, wherein the rear portion includes a sharp edge portion and the fore portion includes a substantially cylindrical portion, wherein the sharp edge portion of the rear portion of the cavity in the trailing edge region has a curved and/or twist shape with a sharp edge at an end, said impingement tube being formed from at least two separate sections corresponding to a rear section and a fore section that are configured to extend span wise through the hollow aerofoil, wherein the rear and fore sections respectively have substantially a same contour as the respective rear and fore portions of the cavity, wherein the rear and fore sections of the impingement tube are connected together by a locking device, said locking device being insertable into the hollow aerofoil so as to urge the rear and fore sections of the impingement tube into locking engagement with portions of the interior surfaces that define the opposed rear and fore portions of the cavity of the hollow aerofoil, wherein said locking device is a roll pin being located in an axially direction between the rear and fore sections of the impingement tube and has a main extension which extends in a radial direction of the hollow aerofoil.