초록 ▼

This invention relates to a method and an apparatus for the cooling of the casing (1) of the turbines (2, 3) of jet engines, in which cooling air is diverted from a bypass flow and supplied to the outer side of the casing via an inlet duct (8) provided with a shut-off element (5). According to the p

This invention relates to a method and an apparatus for the cooling of the casing (1) of the turbines (2, 3) of jet engines, in which cooling air is diverted from a bypass flow and supplied to the outer side of the casing via an inlet duct (8) provided with a shut-off element (5). According to the present invention, the cooling air is supplied to a first chamber (6) in which it is divided by volume. One portion of the cooling air is issued to the casing (1) via orifice holes (10), while another portion is ducted via several tubes (9) to a second chamber (7) which annularly encloses the casing (1) in the area of a low-pressure turbine (3).

대표청구항 ▼

1. A method for the cooling of a casing of turbines of a jet engine, in which cooling air is diverted from a bypass flow and supplied to an outer side of the casing via an inlet duct provided with a shut-off element, wherein the cooling air is fed into a first chamber in which the cooling air is div

1. A method for the cooling of a casing of turbines of a jet engine, in which cooling air is diverted from a bypass flow and supplied to an outer side of the casing via an inlet duct provided with a shut-off element, wherein the cooling air is fed into a first chamber in which the cooling air is divided by volume, one portion of the cooling air being issued from the first chamber to the outer side of the casing and another portion being ducted to a second chamber downstream of the first chamber and being applied to the outer side of the casing from said second chamber. 2. A method in accordance with claim 1, wherein the respective cooling air is discharged upon application to the outer side of the casing. 3. A method in accordance with claim 1, wherein the chambers act as buffer chambers. 4. A method in accordance with claim 1, wherein the cooling air is issued from the chambers via orifices. 5. A method in accordance with claim 1, wherein the cooling air is discharged downstream into a core engine area upon impingement onto the outer side of casing. 6. An apparatus for the cooling of the a casing of turbines of a jet engine with at least one inlet duct for the conduction of cooling air from a bypass flow and with at least one shut-off element associated with the inlet duct, wherein the inlet duct leads into at least one first buffer chamber which is provided with exit holes for the application of cooling air to an outer side of the casing and is connected to at least one tube to supply a portion of the cooling air into at least a second buffer chamber, the second buffer chamber being provided with exit holes for the application of cooling air to the outer side of the casing. 7. An apparatus in accordance with claim 6, wherein the first buffer chamber and the second buffer chamber are designed at least partially annular. 8. An apparatus in accordance with claim 6, wherein the first buffer chamber and the second buffer chamber are designed as annular chambers. 9. An apparatus in accordance with claim 6, wherein several tubes are circumferentially distributed around the casing. 10. An apparatus in accordance with claim 6, wherein the first buffer chamber is provided with orifice holes towards the outer side of the casing. 11. An apparatus in accordance with claim 6, wherein the first buffer chamber and the second buffer chamber are sealed upstream towards the casing. 12. An apparatus in accordance with claim 6, wherein the second buffer chamber is open downstream. 13. An apparatus in accordance with claim 6, wherein the second buffer chamber contains at least one baffle. 14. An apparatus in accordance with claim 6, wherein the first buffer chamber is associated with a high-pressure turbine. 15. An apparatus in accordance with claim 6, wherein the second buffer chamber is associated with a low-pressure turbine. 16. An apparatus in accordance with claim 6, wherein several buffer chambers are arranged on the circumference of the casing. 17. An apparatus in accordance with claim 6, wherein several buffer chambers are arranged behind the other in the direction of the flow. 18. An apparatus in accordance with claim 6, wherein the tube is slideably connected with at least one buffer chamber to compensate for thermal expansion.