초록 ▼

An anti-icing system for a rotating blunt nose bullet of a gas turbine engine uses a rotating thermosyphon effect to create a circulation within a chamber connected for rotation with the nose bullet which draws hot air from a downstream region of the engine forwards to impinge on the nose bullet ove

An anti-icing system for a rotating blunt nose bullet of a gas turbine engine uses a rotating thermosyphon effect to create a circulation within a chamber connected for rotation with the nose bullet which draws hot air from a downstream region of the engine forwards to impinge on the nose bullet over a small region close to the engine axis. This avoids complications with separate hot air supplies or electrical heaters. As shown in FIGS. 3 and 4 of the drawings, in one embodiment of the invention the chamber consists simply of a tube closed off by the nose bullet and in combination with an engine main shaft which extends to the turbine region of the engine to draw hot gas from this region. Alternatively, the chamber may extend only to the downstream end of the first compressor.

대표청구항 ▼

1. A gas turbine engine having a nose bullet rotatable about a longitudinal axis of the engine and an anti-icing system for the nose bullet, said anti-icing system comprising: a chamber rotating with said nose bullet and having a rearward region which is relatively hotter than a forward region of

1. A gas turbine engine having a nose bullet rotatable about a longitudinal axis of the engine and an anti-icing system for the nose bullet, said anti-icing system comprising: a chamber rotating with said nose bullet and having a rearward region which is relatively hotter than a forward region of said chamber; said nose bullet having inner and outer skins defining a space therebetween, said space having a forwardly located sub-chamber therein adjacent to a central region of said nose bullet to be heated, said space providing communication between said sub-chamber of said nose bullet and the rearward region of said chamber; and wall means for defining a conduit for gas circulating within said chamber, said wall means having an upstream end terminating adjacent to and communicating with said sub-chamber and a downstream end with passage means adjacent thereto for providing communication between said wall means and said rearward region of said chamber, no cross-sectional diameter of said upstream end of said wall means being greater than a cross-sectional diameter downstream thereof, and said cross-sectional diameter of said upstream end being less than that of said downstream end; said wall means constraining said gas to flow toward said upstream end and into said sub-chamber for de-icing said central region, said gas being cooled by contact with said central region of said nose bullet and centrifuged radially outwardly due to rotation of said chamber through said space and into the relatively hotter region of said chamber for heating therein, said chamber constraining said gas to flow through said passage means and into the downstream end of said wall means, thereby creating a thermosyphon effect to induce the gas to recirculate at least in part from said relatively hotter region of said chamber and through said wall means to impinge on said central region of said nose bullet. 2. The gas turbine engine of claim 1, wherein the wall means has an end wall at its downstream end thereby closing the chamber. 3. The gas turbine engine of claim 1, wherein the downstream end of the wall means is open-ended such that said wall means communicates with an environment exterior of said chamber, said gas flowing into said wall means through said passage means and said downstream end. 4. The gas turbine of claim 1, wherein the wall means is a centrally located conduit coaxial with said longitudinal axis of said nose bullet. 5. The gas turbine of claim 1, wherein the central region of said nose bullet to be heated has a surface area of three to four square inches, the heating of said central region inhibiting ice formation on the remaining surface area of said nose bullet. 6. The gas turbine engine of claim 1, wherein the cross-sectional diameter of said wall means increases in steps from said upstream end to said downstream end. 7. The gas turbine engine of claim 1, wherein the engine has at least in part a hollow main shaft, and said wall means includes a tube mounted coaxially on said shaft and connected between the shaft and the central region of the nose bullet.