초록

A casing section (30) for rotary apparatus (13, 14) of a gas turbine engine (10) is described. The casing section (30) comprises a partially circumferential casing member (32) and a plurality of radially inwardly extending vanes ( 34) fixed on the casing member (32).

대표청구항 ▼

What is claimed is: 1. A casing section for a rotary apparatus of a gas turbine engine of the type having a rotor carrying rotor blades, the casing section comprising a partially circumferential casing member, the casing member having at least one radially inwardly extending vane, said vane and sai

What is claimed is: 1. A casing section for a rotary apparatus of a gas turbine engine of the type having a rotor carrying rotor blades, the casing section comprising a partially circumferential casing member, the casing member having at least one radially inwardly extending vane, said vane and said casing section being integrally cast as a unit and the casing member having a radially inner face defining a recessed portion for receiving an abradable lining in the recessed portion to provide a seal with the rotor blades. 2. A casing section according to claim 1 wherein the casing section includes a plurality of said radially inwardly extending vanes, each of which is fixed on the casing member. 3. A casing section according to claim 2 wherein a radially inner member is provided, the inner member extending across the radially inner ends of said plurality of vanes so as to comprise a platform. 4. A casing section according to claim 3 characterised in that a sealing means extends radially inwardly from the inner member to sealingly engage a portion of a support member upon which upstream or downstream rotor blades are supported. 5. A casing section according to claim 1 wherein securing means is provided to secure the casing section to an adjacent further casing or casing section. 6. A casing section according to claim 5 wherein securing means comprises at least one flange extending axially across the casing member to secure the casing section to a further circumferentially adjacent casing section. 7. A casing section according to claim 6 wherein the securing means comprises two of said axially extending flanges, one at each axially extending end of the casing member. 8. A casing section according to claim 7 wherein vibration reducing means are arranged in engagement with said axially or circumferentially extending flanges. 9. A casing section according to claim 8 wherein the vibration reducing means comprises one or more gaskets. 10. A casing section according to claim 6 wherein the, or each, flange defines one or more apertures to receive fastening means therethrough. 11. A casing section according to claim 6 wherein the securing means includes a single flange, such flange being arranged along one of the axially extending edges of the casing member, the casing section being securable to a circumferentially adjacent casing section at said single flange. 12. A casing section according to claim 6 wherein the securing means further includes a circumferentially extending flange provided on a circumferentially extending edge of the casing member for securing the casing section to an article arranged upstream or downstream of said casing section. 13. A casing section according to claim 12 wherein a flange is provided on each of the circumferentially extending edges and each flange defines one or more apertures to receive therethrough fastening means to secure the casing section to said upstream or downstream article. 14. A casing section according to claim 1 wherein a radially inner member is provided on the radially inner end of the, or each, vane, said inner member comprising a platform. 15. A casing section according to claim 1 wherein the casing member has an abradable lining provided in the recessed portion to provide a seal with the rotor blades. 16. A vane assembly comprising a plurality of casing sections as claimed in claim 1 secured to each other in an annular array. 17. Rotary apparatus for a gas turbine engine incorporating a vane assembly as claimed in claim 16. 18. Rotary apparatus according to claim 17 in the form of a compressor. 19. A gas turbine engine incorporating rotary apparatus as claimed in claim 17. 20. A casing section for a rotary apparatus of a gas turbine engine of the type having a rotor carrying rotor blades, the casing section comprising a partially circumferential casing member, the casing member having at least one radially inwardly extending vane, said vane being integrally formed during casting with the casing section wherein the casing member and the at least one vane are cast together as a unit and the casing member having a radially inner face defining a recessed portion for receiving an abradable lining in the recessed portion to provide a seal with the rotor blades characterised in that the casing member includes an abradable lining material provided in each of the recessed portions wherein the recessed portions are respectively provided upstream and downstream of the vanes.