GB1072145A - Fluid flow machine for exampls a gas turbine engine or lift fan - Google Patents
Fluid flow machine for exampls a gas turbine engine or lift fanInfo
- Publication number
- GB1072145A GB1072145A GB1376465A GB1376465A GB1072145A GB 1072145 A GB1072145 A GB 1072145A GB 1376465 A GB1376465 A GB 1376465A GB 1376465 A GB1376465 A GB 1376465A GB 1072145 A GB1072145 A GB 1072145A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blades
- rotor
- stator
- gas turbine
- rotor blades
- 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
- 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
- F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1,072,145. Gas turbine engines; axial-flow fans and compressors. ROLLS ROYCE Ltd. March 11, 1966 [March 31, 1965], No. 13764/65. Headings F1C, F1G and F1T. [Also in Division F2] In a fluid flow machine, for example a compressor or a turbine of a gas turbine engine, having at least one stage of adjacently disposed stator vanes and rotor blades, the ratio of the number of stator vanes to the number of rotor blades in the or each stage is given by 1À1n (1 + M) where n is the number of the harmonic which it is desired to eliminate together with any lower harmonies, and M is the rotor blade tip Mach. number at the speed up to which the desired elimination is required, M being calculated in relation to the medium in which the rotor is working. In the gas turbine engine shown the compressor has two rows of stator blades 16 and 18 with a row of rotor blades 17 there-between, there being nineteen blades in the rotor blade row 17. The Mach. number (M) of the tip speed of the rotor blades 17 at the speed for which it is desired to eliminate the fundamental harmonic is 0À8 so substituting in the formula the required ratio of the stator blades 16 to rotor blades 17 is (1À1) (1) (1À8) =1À98 so that the number of stator blades required is (1À98) (19) = 37À6. The number of blades was thus 38 in both stator blade rows 16 and 18, the most suitable angular disposition being found by experiment. The rotor blades may be formed with a hollow internal cavity and apertures by which boundary layer suction may be applied thus tending to remove wakes and turbulence.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1376465A GB1072145A (en) | 1965-03-31 | 1965-03-31 | Fluid flow machine for exampls a gas turbine engine or lift fan |
DE19661476877 DE1476877B2 (en) | 1965-03-31 | 1966-03-24 | Turbo machine, in particular gas turbine jet engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1376465A GB1072145A (en) | 1965-03-31 | 1965-03-31 | Fluid flow machine for exampls a gas turbine engine or lift fan |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1072145A true GB1072145A (en) | 1967-06-14 |
Family
ID=10028949
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1376465A Expired GB1072145A (en) | 1965-03-31 | 1965-03-31 | Fluid flow machine for exampls a gas turbine engine or lift fan |
Country Status (2)
Country | Link |
---|---|
DE (1) | DE1476877B2 (en) |
GB (1) | GB1072145A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2259334A (en) * | 1991-09-06 | 1993-03-10 | Gen Electric | Low noise fan assembly. |
US7806651B2 (en) | 2004-04-02 | 2010-10-05 | Mtu Aero Engines Gmbh | Method for designing a low-pressure turbine of an aircraft engine, and low-pressure turbine |
WO2014159206A1 (en) | 2013-03-14 | 2014-10-02 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
WO2014186017A2 (en) | 2013-03-13 | 2014-11-20 | United Technologies Corporation | Low noise compressor for geared gas turbine engine |
US11719161B2 (en) | 2013-03-14 | 2023-08-08 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014009735B4 (en) | 2014-07-02 | 2021-07-15 | Rosswag Gmbh | Impeller of a turbomachine |
DE102014012480B4 (en) | 2014-08-27 | 2016-06-09 | Rosswag Gmbh | Manufacturing process for a blading of a turbomachine, blading a turbomachine and impeller |
-
1965
- 1965-03-31 GB GB1376465A patent/GB1072145A/en not_active Expired
-
1966
- 1966-03-24 DE DE19661476877 patent/DE1476877B2/en active Pending
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2681099A1 (en) * | 1991-09-06 | 1993-03-12 | Gen Electric | MOUNTING A LOW NOISE BLOWER. |
GB2259334B (en) * | 1991-09-06 | 1995-05-24 | Gen Electric | Low noise fan assembly |
GB2259334A (en) * | 1991-09-06 | 1993-03-10 | Gen Electric | Low noise fan assembly. |
US7806651B2 (en) | 2004-04-02 | 2010-10-05 | Mtu Aero Engines Gmbh | Method for designing a low-pressure turbine of an aircraft engine, and low-pressure turbine |
US10337407B2 (en) | 2013-03-13 | 2019-07-02 | United Technologies Corporation | Low noise compressor for geared gas turbine engine |
EP4163479A1 (en) * | 2013-03-13 | 2023-04-12 | Raytheon Technologies Corporation | Low noise compressor for geared gas turbine engine |
WO2014186017A2 (en) | 2013-03-13 | 2014-11-20 | United Technologies Corporation | Low noise compressor for geared gas turbine engine |
EP2971658A4 (en) * | 2013-03-13 | 2016-11-16 | United Technologies Corp | Low noise compressor for geared gas turbine engine |
EP2971512A4 (en) * | 2013-03-14 | 2016-11-09 | United Technologies Corp | Low noise turbine for geared gas turbine engine |
US10533447B2 (en) | 2013-03-14 | 2020-01-14 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
US10605172B2 (en) | 2013-03-14 | 2020-03-31 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
US11143109B2 (en) | 2013-03-14 | 2021-10-12 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
US11560849B2 (en) | 2013-03-14 | 2023-01-24 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
WO2014159206A1 (en) | 2013-03-14 | 2014-10-02 | United Technologies Corporation | Low noise turbine for geared gas turbine engine |
US11719161B2 (en) | 2013-03-14 | 2023-08-08 | Raytheon Technologies Corporation | Low noise turbine for geared gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
DE1476877B2 (en) | 1970-10-01 |
DE1476877A1 (en) | 1970-02-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1291943A (en) | Improvements in or relating to ducted fans | |
GB1487324A (en) | Gas turbine engines | |
GB992941A (en) | Improvements in rotary bladed compressors and turbines | |
US3617147A (en) | Fluid flow machine | |
GB1386481A (en) | Low noise ducted fan assembly | |
GB1271819A (en) | Improvements in film cooling of structural members in gas turbine engines | |
GB1514613A (en) | Blade or vane for a gas turbine engine | |
GB1177665A (en) | Improvement in or relating to Turbines, Compressors and like Bladed Rotary Fluid Flow Machines. | |
GB1505534A (en) | Turbines and compressors | |
US4318669A (en) | Vane configuration for fluid wake re-energization | |
GB1457634A (en) | Converging-diverging supersonic nozzles | |
GB742477A (en) | Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors | |
GB1314853A (en) | Stator blading for turbomachinery | |
GB1072145A (en) | Fluid flow machine for exampls a gas turbine engine or lift fan | |
GB855058A (en) | Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines | |
GB1350424A (en) | Cooled blade for a gas turbine engine | |
GB1342590A (en) | Suppression of noise in gas turbine engines | |
GB1085227A (en) | Improvements in or relating to gas turbine engines | |
GB767656A (en) | Improvements in or relating to axial-flow fluid machines such as turbines and compressors | |
KR930021928A (en) | Axial flow turbine | |
GB1119479A (en) | Improvements in multi-stage axial flow compressors | |
GB777955A (en) | Improvements in or relating to fluid flow machines such as hydraulic, steam or gas turbines or axial-flow compressors | |
GB1231424A (en) | ||
US3580692A (en) | Seal construction | |
GB986797A (en) | Improvements in and relating to machines comprising a bladed rotor such as water turbines and pumps |