Rolls-royce Corporation

Caner Hasan Helvaci

Ian Tibbott

Roderick M Townes

Dougal Richard Jackson

Stephen Christopher Diamond

Brian G Cooper

Edwin Dane

Adrian J Webster

Glenn R Paxton

Glenn Paxton

Roderick Miles Townes

Adrian Joseph Webster

Ian Tibbot

Stephen Diamon

A computer-based method of designing a guide vane formation is provided. The vane formation is for use in a gas turbine engine which has a cascade of circumferentially arranged identical guide vane formations. The vane formation has radially inner and radially outer chordal seals. The method allows the elimination of 'saw-tooth' leakage gaps between inner chordal seals of neighboring vane formations and between outer chordal seals of neighboring vane formations even when the inner and outer chordal seals are axially offset from each other.

Method of designing guide vane formations

A biasing means is provided for securing a plurality of sealing components which are arranged to seal gaps between adjacent structural components in a turbine, the biasing means having three foot regions joined in a substantially linear fashion by two resilient curved arms, wherein each arm has securing means for securing the biasing means to one of said structural components such that when the biasing means is secured to said one of said structural components, each of said foot regions contacts one of said sealing components and the curved arms urge the sealing components towards one of said structural components so that the sealing components collectively create a seal over the gap between said structural components. An apparatus for sealing gaps between adjacent structural components which includes the biasing means is also provided as is a method of sealing gaps in a turbine.

Flap seal spring and sealing apparatus

A sealing plate for sealing a gap between two primary sealing plates is provided. The sealing plate has a sealing portion and a connector portion, wherein the sealing portion has a width which is greater than a width of the connector portion. An apparatus for sealing a gap between two structural components of a turbine, the apparatus including a plurality of primary sealing components, and at least one sealing plate is also provided, as is a turbine having a plurality of structural components with a gap between said structural components, wherein the gap is sealed by a plurality of sealing components, the sealing components comprising a plurality of primary sealing components and at least one sealing plate.

Flap seal and sealing apparatus

A rotor bladefor a gas turbine engine has an aerofoil portionfrom a rootto a tip. In use, combustion gas may leak over the tipfrom the pressure faceto the suction face. A gutterextends across the tipto entrain any over tip leakage gap. The floor of the gutter defines an increased depth portionat the exit end of the gutter

Blades

A turbine blade for a gas turbine engine has an aerofoil portion extending from a root to a tip. The tip carries winglets. A gutter extends across the tip to entrain gas leaking around the tip (over tip leakage). The aerofoil portion has a mean camber line and the gutter has a center line. In the examples described, the conditions that (a) the mean camber line and the centre line coincide at the exit when viewed from the tip towards the root, and (b) the mean camber line and the center line are parallel at the exit when viewed as aforesaid, are not both fulfilled.

Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.

Cooling arrangements

A turbine blade damper arrangement in which a damper is positioned against the undersides of the platforms of adjacent turbine blades. In operation, the damper is centrifugally urged into engagement with the blade platforms to provide damping of relative movement between the blades. The damper and platform surfaces that it engages are of part-cylindrical configuration in order to minimize gas leakage paths between the damper and blade platforms.

Turbine blade damper arrangement

Dampers () are utilized with regard to mounting arrangements () in gas turbine engines () in order to facilitate cooling. It is known to provide slotted upper surface or cottage roof dampers to enhance cooling effect. However, cooling efficiency cannot be optimized and improving cooling effectiveness particularly between the parts of a mounting arrangement can be difficult without detrimental reductions in overall efficiency of a gas turbine engine () incorporating such a mounting. By provision of impingement jets () which extend through the damper () into slots () which define an upper surface of the damper () improvements in cooling efficiency can be achieved. The slots () are typically closed to reduce requirements with respect to pressure differentials. However, open ended slots () with impingement jets () can also be provided. Typically, the slots () extend laterally across the dampers () but could also extend longitudinally with closed ends or one end open. By such an approach improved heat transfer is achieved without necessary increases in pressure gradients and flow rates.

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Derby, United Kingdom

Caner Hasan Helvaci