US2445837A - Air-cooled gas turbine - Google Patents
Air-cooled gas turbine Download PDFInfo
- Publication number
- US2445837A US2445837A US692802A US69280246A US2445837A US 2445837 A US2445837 A US 2445837A US 692802 A US692802 A US 692802A US 69280246 A US69280246 A US 69280246A US 2445837 A US2445837 A US 2445837A
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- Prior art keywords
- air
- turbine
- drums
- casing
- rings
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Classifications
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- 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
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
Definitions
- An object of theinvention is to provide an improved impulse type air-cooled gas turbine.
- Another object or the invention is to provide signed to give the least wind'resistance possible at I the tips of the blades, which would otherwise be in danger of shearing 0115 due to windage.
- a still further object oi'the invention is to provide a multiple stage impulse type air-cooled gas turbine having automatically controlled means for cooling the turbine blades and the labyrinth packings about the hollow shaft and between the drums of the turbine, with an air compressor being connected to the combustion chamber of said turbine and having lines or pipes with reducing valves connected with said labyrinth packings 30 at the opposite sides of said rings to prevent leak age of contaminated gases into the cleanair, and also to increase the efliciency of the turbine.
- FIG. 1 is a schematic vertical sectional view through the improved impulse type air-cooled gas turbine
- Figure 2 is a plan view looking down on one 01' the turbine drums and rings, the same being partly broken away to show the cross-sectional shape of the hollow turbine blades:
- Figure 31 s a vertical sectional view through one of the turbine drums, being partly broken away 'and in section to show the arrangement of the air-cooled turbine blades and holding ring;
- an improved impulse type air-cooled gas turbine I an improved multiple stage impulse type airhaving a casing generally denoted by the reference numeral I, and a longitudinally extending hollow shaft 2 having flared ends 3 and 4 at its opposite ends, being adapted to receive the oppositely disposed funnel-shaped air inlet housings 5 and 6 whose reduced inner'ends 'l and I are supported upon the frame members 9 and II disposed on the base standards II and I2.
- the three stage impulse type air-cooled gas turbine islprovided with the rotatably mounted drums l3, ll and I5, each of which is received in a suitable recess in the casing l, and are open at their central portions to receive air from the air inlet passages or apertures, it formed through the wall of thehollow shaft 2.
- Annular internal webs ll are formed in each drum II, II and i5, and are aperturedat It to allow air to pass therethrough' to the radially extending hollow turbine blades is supported about said drums and cooperating with the holding rings 20 which are labyrinth packed and ported at 2
- the turbine blades is arcuately curved, of the drawings.
- a combustion chamber 22 is secured to the end 01' the casing I by means of the bolts 23 and connects through the nozzle 24 with the turbine blades on the first stage drum II, to direct the combusare transversely and as clearly-shown in Figure 4 tion gases at an approximate pressure of 150 pounds against and through said blades.
- the gases pass through the blades on drum [3, the pressure will have dropped to approximately 100 pounds to be discharged through the nozzle 25 drum Itto and through the blades on the second stage
- the combustion gases will then drop to approximately pounds and be discharged 1 through the nozzle 26 to and through theblades on the third stage drum Ii, to be exhausted into Figure 4 is a plan view looking down on a hol- 50 the atmosphere or auxiliary heat transfer units where remaining heat may be utilized for other purposes.
- the air casing or chamber 21 will be formed about the holding rings 20 to receive the air sucked through the turbine blades and rings 2!, to be led through the pipe 28 into the funnel 2! on the air inlet pipe 30 connected with the air compressor 3L.
- the air compressor II will be connected by meansof the pipe 32 with the out the following specification and the accomcombustion chamber to discharge air thereto at from a suitable fuel pump and supply tank (not shown).
- a compressed air pipe line 35 will branch from a the air pipe 32, and will be provided with the three reducing valves 35, 31 and 38, which in turn have pipe lines extending to the combustion chamber side of the labyrinth packing 39 on the first stage holding ring 20 and to the labyrinth packing 40 on the hollow shaft 2, to the adjacent sides of the labyrinth packings ll and 42 on the holding ring 20 on the second stage and to the labyrinth packing 43 on said hollow shaft, and finally to the labyrinth packings l4 and 45 on the holding ring 20 on the third stage and to the labyrinth packing 46 on said hollow shaft 2.
- the combustion gases will reach the three stages or drums at pressures of 150 pounds, 100 pounds and 50 pounds, respectively, while the reducing valves will direct the air at pressures of 175 pounds, 125 pounds, 75 pounds and 25 pounds to the various labyrinth packings to oppose and preventany leakage of the contaminated gases into the fresh air supply to the air compressor.
- An impulse type air-cooled multiple stage gas turbine comprising a casing, a. hollow shaft extending axially therethrough; a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, and labyrinth packing at the opposite sides of said drums and said rings.
- An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an 'air compartment about said rings, controlled means for cooling said
- a suitable drive (not shown) will be connected with the hollow shaft upon which the turbine drums are mounted to operate any desired mechanism.
- An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said.
- An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said combustion chamber, means connected with said air compressor for cooling said labyrinth packings, and valves in the ends of said hollow'shaft hollow turbine blades supported by said drums,
- An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said combustion chamber, means connected with said air compressor for cooling said labyrinth packings, valves in the ends of said hollow shaft to control the admission of air to and through said turbine drums and blades, and bulbs in said air compartment connected with thermostats for controlling said valves and the admission of air 10 to and through said turbine drums and blades.
Description
J y 'r. M. MCKENZIE, JR 2,445,837
AIR .COOLED GAS TURBINE Filed Aug. 24, 1946 2 Sheets- Sheet 1 l B a WWW July 27, 1948. T. M. MCKENZIE, JR
AIR COOLED GAS TURBINE 2 Sheets-Sheep 2 Filed Aug. 24, 1946 nuannuflu H v m M i w I part or this application:
. Patented July 27, 1948 UNITED STATES PATENT- orricr.
AIR-COOLED GAS TURBINE Thomas M. McKenzie, Jr., Hyattsville, Md. Application August 24, 1946, Serial No. 692,802
7 Claims. (CI. 60-41) This invention relates to improvements in aircooled gas turbines.
An object of theinvention is to provide an improved impulse type air-cooled gas turbine.
- Another object or the invention is to provide signed to give the least wind'resistance possible at I the tips of the blades, which would otherwise be in danger of shearing 0115 due to windage.
' A still further object oi'the invention is to provide a multiple stage impulse type air-cooled gas turbine having automatically controlled means for cooling the turbine blades and the labyrinth packings about the hollow shaft and between the drums of the turbine, with an air compressor being connected to the combustion chamber of said turbine and having lines or pipes with reducing valves connected with said labyrinth packings 30 at the opposite sides of said rings to prevent leak age of contaminated gases into the cleanair, and also to increase the efliciency of the turbine.
Other objects will appear as the description proceeds. v
In the accompanying drawings which form a V Figure 1 is a schematic vertical sectional view through the improved impulse type air-cooled gas turbine; Figure 2 is a plan view looking down on one 01' the turbine drums and rings, the same being partly broken away to show the cross-sectional shape of the hollow turbine blades:
Figure 31s a vertical sectional view through one of the turbine drums, being partly broken away 'and in section to show the arrangement of the air-cooled turbine blades and holding ring;
, panying drawings to designate corresponding In carrying out the invention, there is provided an improved impulse type air-cooled gas turbine I an improved multiple stage impulse type airhaving a casing generally denoted by the reference numeral I, and a longitudinally extending hollow shaft 2 having flared ends 3 and 4 at its opposite ends, being adapted to receive the oppositely disposed funnel-shaped air inlet housings 5 and 6 whose reduced inner'ends 'l and I are supported upon the frame members 9 and II disposed on the base standards II and I2.
The three stage impulse type air-cooled gas turbine islprovided with the rotatably mounted drums l3, ll and I5, each of which is received in a suitable recess in the casing l, and are open at their central portions to receive air from the air inlet passages or apertures, it formed through the wall of thehollow shaft 2.
Annular internal webs ll are formed in each drum II, II and i5, and are aperturedat It to allow air to pass therethrough' to the radially extending hollow turbine blades is supported about said drums and cooperating with the holding rings 20 which are labyrinth packed and ported at 2| to hold the turbine blades in place and to suck the air into the turbine blades.
The turbine blades is arcuately curved, of the drawings.
A combustion chamber 22 is secured to the end 01' the casing I by means of the bolts 23 and connects through the nozzle 24 with the turbine blades on the first stage drum II, to direct the combusare transversely and as clearly-shown in Figure 4 tion gases at an approximate pressure of 150 pounds against and through said blades. After the gases pass through the blades on drum [3, the pressure will have dropped to approximately 100 pounds to be discharged through the nozzle 25 drum Itto and through the blades on the second stage The combustion gases will then drop to approximately pounds and be discharged 1 through the nozzle 26 to and through theblades on the third stage drum Ii, to be exhausted into Figure 4 is a plan view looking down on a hol- 50 the atmosphere or auxiliary heat transfer units where remaining heat may be utilized for other purposes. V
The air casing or chamber 21 will be formed about the holding rings 20 to receive the air sucked through the turbine blades and rings 2!, to be led through the pipe 28 into the funnel 2! on the air inlet pipe 30 connected with the air compressor 3L. The air compressor II will be connected by meansof the pipe 32 with the out the following specification and the accomcombustion chamber to discharge air thereto at from a suitable fuel pump and supply tank (not shown).
A compressed air pipe line 35 will branch from a the air pipe 32, and will be provided with the three reducing valves 35, 31 and 38, which in turn have pipe lines extending to the combustion chamber side of the labyrinth packing 39 on the first stage holding ring 20 and to the labyrinth packing 40 on the hollow shaft 2, to the adjacent sides of the labyrinth packings ll and 42 on the holding ring 20 on the second stage and to the labyrinth packing 43 on said hollow shaft, and finally to the labyrinth packings l4 and 45 on the holding ring 20 on the third stage and to the labyrinth packing 46 on said hollow shaft 2.
As before mentioned, the combustion gases will reach the three stages or drums at pressures of 150 pounds, 100 pounds and 50 pounds, respectively, while the reducing valves will direct the air at pressures of 175 pounds, 125 pounds, 75 pounds and 25 pounds to the various labyrinth packings to oppose and preventany leakage of the contaminated gases into the fresh air supply to the air compressor.
The entrance of air at atmospheric pressure into the opposite ends of the hollow shaft will be controlled vbythe butterfly valves 41 and 48 connected by the arms 49 and 50 with the bellows type thermostats and 52, which are in turn connected by means of the small pipes 58 and 54 with the bulbs 55 and 56 extending through the walls of the air casing or chamber 21, whereby the temperature of the air which varies at the opposite ends of the air chamber will be kept at an approximately even level. Coil springs 51 and 58 will be secured to the arms 49 to urge the butterfly valves .41 and 45 toward their closed positions.
From the foregoing description, it will be apparent that the air pressure from the air compressor will always be materially more than the pressure of the combustion gases at the various stages of the turbine where the compressed air.
is led to the labyrinth packings, thereby forcing back and preventing the contaminated combustion gases from entering into the fresh clean air which is fed back to theair compressor.
2. An impulse type air-cooled multiple stage gas turbinecomprising a casing, a. hollow shaft extending axially therethrough; a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, and labyrinth packing at the opposite sides of said drums and said rings.
3. An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an 'air compartment about said rings, controlled means for cooling said A suitable drive (not shown) will be connected with the hollow shaft upon which the turbine drums are mounted to operate any desired mechanism. 1
While the preferred embodiment of the instant invention has been illustrated and described, it
will be understood that it is not intended to limit the scope of the invention thereto, as many minor changes in detail of construction may be resorted to without departure from the spirit of a turbine blades, labyrinth packings at the opposite sides of said drums and said rings, and an air compressor having its inlet connected with said air compartment and its outlet connected with said combustion chamber.
4. An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said.
combustion chamber, and means connected with said air compressor for cooling said labyrinth packings and to prevent leakage of hot contaminated gases into the clean air supply.
5. An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said combustion chamber, means connected with said air compressor for cooling said labyrinth packings, and valves in the ends of said hollow'shaft hollow turbine blades supported by said drums,
ported holding rings sposed about the outer ends of said turbine blades, an air compartment about said rings, and controlled means for cooling said turbine blades,
to control the admission of air to and through said turbine drums and blades.
6. An impulse type air-cooled multiple stage gas turbine comprising a casing, a hollow shaft extending axially therethrough, a combustion chamber on said casing, multiple stage turbine drums rotatably mounted in said casing having communication with said hollow shaft, hollow turbine blades supported by said drums, ported holding rings disposed about the outer ends of said turbine blades, an air compartment about said rings, controlled means for cooling said turbine blades, labyrinth packings at the opposite sides of said drums and said rings, an air compressor having its inlet connected with said air compartment and its outlet connected with said combustion chamber, means connected with said air compressor for cooling said labyrinth packings, valves in the ends of said hollow shaft to control the admission of air to and through said turbine drums and blades, and bulbs in said air compartment connected with thermostats for controlling said valves and the admission of air 10 to and through said turbine drums and blades.
7. The subject matter as claimed in claim 4, and air lines from said air compressor having reducing valves connected with said labyrinth packings for directing a pressure thereto greater than the pressure of. the combustion gases to prevent the contaminated gases from entering the air compressor with the fresh air.
THOMAS M. MCKENZIE, JR.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US692802A US2445837A (en) | 1946-08-24 | 1946-08-24 | Air-cooled gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US692802A US2445837A (en) | 1946-08-24 | 1946-08-24 | Air-cooled gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2445837A true US2445837A (en) | 1948-07-27 |
Family
ID=24782077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US692802A Expired - Lifetime US2445837A (en) | 1946-08-24 | 1946-08-24 | Air-cooled gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2445837A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2618120A (en) * | 1946-06-07 | 1952-11-18 | Papini Anthony | Coaxial combustion products generator and turbine with cooling means |
| US2627161A (en) * | 1947-04-03 | 1953-02-03 | Jarvis C Marble | Elastic fluid power system utilizing a rotary engine with cooled rotors |
| US2669420A (en) * | 1948-07-03 | 1954-02-16 | Kellogg M W Co | Turbine structure |
| US2791091A (en) * | 1950-05-15 | 1957-05-07 | Gen Motors Corp | Power plant cooling and thrust balancing systems |
| US2811833A (en) * | 1953-06-05 | 1957-11-05 | Gen Motors Corp | Turbine cooling |
| US2841362A (en) * | 1952-04-14 | 1958-07-01 | Yeomans Clifton | Multistage turbine |
| US2940257A (en) * | 1953-03-27 | 1960-06-14 | Daimler Benz Ag | Cooling arrangement for a combustion turbine |
| US2950598A (en) * | 1954-11-22 | 1960-08-30 | Otto R Nemeth | Air cooled gas turbine power plant |
| US3015937A (en) * | 1958-07-03 | 1962-01-09 | James V Giliberty | Temperature modulating system for internal combustion turbines and the like |
| FR2452599A1 (en) * | 1979-03-30 | 1980-10-24 | Gen Electric | IMPROVED SYSTEM FOR SUPPLYING COOLING AIR TO A TURBOMACHINE |
| WO1997038219A1 (en) * | 1996-04-04 | 1997-10-16 | Westinghouse Electric Corporation | Closed-loop air cooling system for a turbine engine |
| CN102588117A (en) * | 2011-01-13 | 2012-07-18 | 通用电气公司 | Apparatus and method for controlling oxygen emissions from a gas turbine |
| US20160047311A1 (en) * | 2014-08-15 | 2016-02-18 | United Technologies Corporation | Gas turbine engine cooling fluid metering system |
| US10443856B2 (en) * | 2015-02-11 | 2019-10-15 | Rolls-Royce North American Technologies Inc. | Wave rotors with temperature control features |
-
1946
- 1946-08-24 US US692802A patent/US2445837A/en not_active Expired - Lifetime
Non-Patent Citations (1)
| Title |
|---|
| None * |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2618120A (en) * | 1946-06-07 | 1952-11-18 | Papini Anthony | Coaxial combustion products generator and turbine with cooling means |
| US2627161A (en) * | 1947-04-03 | 1953-02-03 | Jarvis C Marble | Elastic fluid power system utilizing a rotary engine with cooled rotors |
| US2669420A (en) * | 1948-07-03 | 1954-02-16 | Kellogg M W Co | Turbine structure |
| US2791091A (en) * | 1950-05-15 | 1957-05-07 | Gen Motors Corp | Power plant cooling and thrust balancing systems |
| US2841362A (en) * | 1952-04-14 | 1958-07-01 | Yeomans Clifton | Multistage turbine |
| US2940257A (en) * | 1953-03-27 | 1960-06-14 | Daimler Benz Ag | Cooling arrangement for a combustion turbine |
| US2811833A (en) * | 1953-06-05 | 1957-11-05 | Gen Motors Corp | Turbine cooling |
| US2950598A (en) * | 1954-11-22 | 1960-08-30 | Otto R Nemeth | Air cooled gas turbine power plant |
| US3015937A (en) * | 1958-07-03 | 1962-01-09 | James V Giliberty | Temperature modulating system for internal combustion turbines and the like |
| FR2452599A1 (en) * | 1979-03-30 | 1980-10-24 | Gen Electric | IMPROVED SYSTEM FOR SUPPLYING COOLING AIR TO A TURBOMACHINE |
| WO1997038219A1 (en) * | 1996-04-04 | 1997-10-16 | Westinghouse Electric Corporation | Closed-loop air cooling system for a turbine engine |
| US6098395A (en) * | 1996-04-04 | 2000-08-08 | Siemens Westinghouse Power Corporation | Closed-loop air cooling system for a turbine engine |
| CN102588117A (en) * | 2011-01-13 | 2012-07-18 | 通用电气公司 | Apparatus and method for controlling oxygen emissions from a gas turbine |
| US20120180493A1 (en) * | 2011-01-13 | 2012-07-19 | General Electric Company | Apparatus and method for controlling oxygen emissions from a gas turbine |
| US20160047311A1 (en) * | 2014-08-15 | 2016-02-18 | United Technologies Corporation | Gas turbine engine cooling fluid metering system |
| US10443498B2 (en) * | 2014-08-15 | 2019-10-15 | United Technologies Corporation | Gas turbine engine cooling fluid metering system |
| US11939919B2 (en) | 2014-08-15 | 2024-03-26 | Rtx Corporation | Gas turbine engine cooling fluid metering system |
| US10443856B2 (en) * | 2015-02-11 | 2019-10-15 | Rolls-Royce North American Technologies Inc. | Wave rotors with temperature control features |
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