High compressor exit guide vane assembly to pre-diffuser junction
A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.
1. A system for a gas turbine engine, comprising
an exit guide vane assembly that includes a first radially inner platform, a first radially outer platform, an axial outlet, and a plurality of exit guide vanes circumferentially distributed between the first radially inner platform and the first radially outer platform,
wherein at the axial outlet, the first radially inner platform includes a first radially inner ring that extends radially inward to a first radially inner end, and a first plurality of tabs extend in an axial downstream direction from the first radially inner end, the first plurality of tabs being circumferentially spaced about the first radially inner end,
a pre-diffuser assembly that includes a second radially inner platform, a second radially outer platform, and an axial inlet,
wherein at the axial inlet, the second radially inner platform includes a second radially inner ring that extends radially inward to a second radially inner end, and a second plurality of tabs extend in an axial upstream direction from the second radially inner end, the second plurality of tabs being circumferentially spaced about the second radially inner end,
wherein when the axial outlet of the exit guide vane is disposed axially against the axial inlet of the diffuser;
the first radially inner ring is radially aligned with, and axially opposes, the second radially inner ring so that the first radially inner ring forms a first inner W-seal land and the second radially inner ring forms a second inner W-seal land, and
the first plurality of tabs are axially aligned with, and circumferentially engage, the second plurality of tabs to prevent rotation of the exit guide vane assembly relative to the pre-diffuser assembly.
2. The system of claim 1 , wherein
at the axial outlet of the exit guide vane, the first radially outer platform includes a first radially outer ring that extends radially outward to a first radially outer end, and
at the axial inlet of the pre-diffuser, the second radially outer platform includes a second radially outer ring that extends radially outward to a second radially outer end,
wherein when the axial outlet of the exit guide vane is disposed axially against the axial inlet of the diffuser:
the first radially outer ring is radially aligned with, and axially opposes, the second radially outer ring so that the first radially outer ring forms a first outer W-seal land and the second radially outer ring forms a second outer W-seal land.
3. The system in accordance with claim 2 , wherein the pre-diffuser and EGV assembly exhibit different thermal expansion rates.
4. The system in accordance with claim 2 , wherein one of the first plurality of tabs and the second plurality of tabs is arranged in pairs, and wherein another of the first plurality of tabs and the second plurality of tabs is arranged so that each tab thereof fits between one of the pairs.
5. The system in accordance with claim 2 , wherein the pre-diffuser is linked to an inner diffuser case, and wherein the inner diffuser case supports the second plurality of tabs.
6. A gas turbine engine, comprising:
a compressor;
an exit guide vane assembly that includes a first radially inner platform, a first radially outer platform, an axial outlet, and a plurality of exit guide vanes circumferentially distributed between the first radially inner platform and the first radially outer platform,
wherein at the axial outlet, the first radially inner platform includes a first radially inner ring that extends radially inward to a first radially inner end, and a first plurality of tabs extend in an axial downstream direction from the first radially inner end, the first plurality of tabs being circumferentially spaced about the first radially inner end,
a pre-diffuser assembly that includes a second radially inner platform, a second radially outer platform, and an axial inlet,
wherein at the axial inlet, the second radially inner platform includes a second radially inner ring that extends radially inward to a second radially inner end, and a second plurality of tabs extend in an axial upstream direction from the second radially inner end, the second plurality of tabs being circumferentially spaced about the second radially inner end,
wherein when the axial outlet of the exit guide vane is disposed axially against the axial inlet of the diffuser:
the first radially inner ring is radially aligned with, and axially opposes, the second radially inner ring so that the first radially inner ring forms a first inner W-seal land and the second radially inner ring forms a second inner W-seal land, and
the first plurality of tabs are axially aligned with, and circumferentially engage, the second plurality of tabs to prevent rotation of the exit guide vane assembly relative to the pre-diffuser assembly.
7. The engine of claim 6 , wherein
at the axial outlet of the exit guide vane, the first radially outer platform includes a first radially outer ring that extends radially outward to a first radially outer end, and
at the axial inlet of the pre-diffuser, the second radially outer platform includes a second radially outer ring that extends radially outward to a second radially outer end,
wherein when the axial outlet of the exit guide vane is disposed axially against the axial inlet of the diffuser:
the first radially outer ring is radially aligned with, and axially opposes, the second radially outer ring so that the first radially outer ring forms a first outer W-seal land and the second radially outer ring forms a second outer W-seal land.
8. The gas turbine engine in accordance with claim 7 , wherein the pre-diffuser and EGV assembly exhibit different thermal expansion rates.
9. The gas turbine engine in accordance with claim 7 , wherein w-seals span first and second gaps respectively between the EGV assembly and the pre-diffuser.
10. The gas turbine engine in accordance with claim 7 , wherein one of the first plurality of tabs and the second plurality of tabs is arranged in pairs, and wherein another of the first plurality of tabs and the second plurality of tabs is arranged so that each tab thereof fits between one of the pairs.
11. The gas turbine engine in accordance with claim 7 , wherein the pre-diffuser is linked to an inner diffuser case, and wherein the inner diffuser case supports the second plurality of tabs.
12. A method of configuring a system for a gas turbine engine, comprising:
providing an exit guide vane assembly that includes a first radially inner platform, a first radially outer platform, an axial outlet, and a plurality of exit guide vanes circumferentially distributed between the first radially inner platform and the first radially outer platform,
wherein at the axial outlet, the first radially inner platform includes a first radially inner ring that extends radially inward to a first radially inner end, and a first plurality of tabs extend in an axial downstream direction from the first radially inner end, the first plurality of tabs being circumferentially spaced about the first radially inner end
providing a pre-diffuser assembly that includes a second radially inner platform, a second radially outer platform, and an axial inlet,
wherein at the axial inlet, the second radially inner platform includes a second radially inner ring that extends radially inward to a second radially inner end, and a second plurality of tabs extend in an axial upstream direction from the second radially inner end, the second plurality of tabs being circumferentially space about the second radially inner end,
disposing the axial outlet of the exit guide vane axially against the axial inlet of the diffuser so that
the first radially inner ring is radially aligned with, and axially opposes, the second radially inner ring so that the first radially inner ring forms a first inner W-seal land and the second radially inner ring forms a second inner W-seal land, and
the first plurality of tabs are axially aligned with, and circumferentially engage, the second plurality of tabs to prevent rotation of the exit guide vane assembly relative to the pre-diffuser assembly; and
allowing differential axial and radial thermal expansion between the pre-diffuser and the EGV assembly.
13. The method in accordance with claim 12 , wherein
at the axial outlet of the exit guide vane, the first radially outer platform includes a first radially outer ring that extends radially outward to a first radially outer end, and
at the axial inlet of the pre-diffuser, the second radially outer platform includes a second radially outer ring that extends radially outward to a second radially outer end,
wherein when the axial outlet of the exit guide vane is disposed axially against the axial inlet of the diffuser:
the first radially outer ring is radially aligned with, and axially opposes, the second radially outer ring so that the first radially outer ring forms a first outer W-seal land and the second radially outer ring forms a second outer W-seal land.
14. The method in accordance with claim 13 , comprising interlocking the first plurality of tabs and the second plurality of tabs.
15. The method in accordance with claim 14 , wherein one of the first plurality of tabs and the second plurality of tabs is arranged in pairs, and wherein another of the first plurality of tabs and the second plurality of tabs is arranged so that each tab thereof fits between one of the pairs.