GB1347514A - Gas turbine plants - Google Patents
Gas turbine plantsInfo
- Publication number
- GB1347514A GB1347514A GB1505271A GB1505271A GB1347514A GB 1347514 A GB1347514 A GB 1347514A GB 1505271 A GB1505271 A GB 1505271A GB 1505271 A GB1505271 A GB 1505271A GB 1347514 A GB1347514 A GB 1347514A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- sector
- cooling air
- duct
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
- F02C3/085—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage the turbine being of the radial-flow type (radial-radial)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/125—Cooling of plants by partial arc admission of the working fluid or by intermittent admission of working and cooling fluid
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1347514 Cooling gas turbine plants SOC RATEAU 14 May 1971 [19 May 1970] 15052/71 Heading F1G In a gas turbine plant having a compressor 6b supplying air to a combustion chamber 15b feeding hot gases to drive a turbine 7b, at least some of the compressed air is fed directly from a sector of the compressor discharge and through a duct 29, substantially without change in temperature and velocity, to a sector of the turbine inlet so that the turbine rotor blades alternately pass through regions of hot gases and cooling air. In the arrangement shown the compressor 6b is centrifugal and feeds a major proportion of its air output via a sector of guide blades 26b and scroll 136 to combustion chamber 15b, the remaining proportion flowing through unbladed sector 29 defined between partitions 27, 28 directly to the corresponding unbladed sector at the inlet to centripetal turbine 7b integral with compressor 6b. More than one direct flow sector may be provided. The annular discharge conduit 21b from turbine 7b is interrupted at its inlet by two partitions (31 and 32), Fig. 3a, (not shown), defining a duct 33 through which the cooling air leaving turbine 7b discharges at 34 to atmosphere. A power turbine 23b is provided. In a modification Fig. 6, (not shown), cooling air duct 29 is supplemented or replaced by extending the radial flow compressor and turbine blades radially beyond the hub (43) to provide an annular space (44) into which a stationary part-annular partition (45) extends. The gap between the ends of the partition provides a duct for the direct flow of cooling air from the compressor to the turbine. In further modifications, Figs. 8 and 9, (not shown) an additional turbine driven axial flow or centrifugal compressor (47) is provided upstream of compressor 6b and the cooling air leaving the turbine is returned to the second stage compressor via a cooler (52). The compressed air may be pre-heated in an exhaust gas heat exchanger (53) before entering the combustion chamber. The radial flow turbine and compressor may be replaced by axial-flow Fig. 7, (not shown).
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR7018122A FR2087405A5 (en) | 1970-05-19 | 1970-05-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1347514A true GB1347514A (en) | 1974-02-27 |
Family
ID=9055690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1505271A Expired GB1347514A (en) | 1970-05-19 | 1971-05-14 | Gas turbine plants |
Country Status (4)
| Country | Link |
|---|---|
| BR (1) | BR7103001D0 (en) |
| DE (1) | DE2124504C2 (en) |
| FR (1) | FR2087405A5 (en) |
| GB (1) | GB1347514A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2469565A1 (en) * | 1979-11-07 | 1981-05-22 | Alsthom Atlantique | COOLING DEVICE FOR A GAS TURBINE GROUP |
| DE3544184A1 (en) * | 1984-01-20 | 1986-05-28 | Franz-Josef 3500 Kassel Weber | Radial gas turbine |
| DE3424853C2 (en) * | 1984-01-20 | 1986-02-13 | Franz-Josef 3500 Kassel Weber | Radial gas turbine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE925984C (en) * | 1941-02-13 | 1955-04-04 | Karl Dr-Ing Leist | Partially loaded gas turbine |
| CH298259A (en) * | 1952-01-11 | 1954-04-30 | Berger Hans | Turbo engine for vehicles. |
-
1970
- 1970-05-19 FR FR7018122A patent/FR2087405A5/fr not_active Expired
-
1971
- 1971-05-14 GB GB1505271A patent/GB1347514A/en not_active Expired
- 1971-05-18 BR BR300171A patent/BR7103001D0/en unknown
- 1971-05-18 DE DE19712124504 patent/DE2124504C2/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| DE2124504A1 (en) | 1972-02-10 |
| BR7103001D0 (en) | 1973-05-10 |
| DE2124504C2 (en) | 1981-09-17 |
| FR2087405A5 (en) | 1971-12-31 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |