US3170295A

US3170295A - Propellant tank pressurization system

Info

Publication number: US3170295A
Application number: US271823A
Authority: US
Inventors: Hugh L Dryden
Original assignee: Individual
Current assignee: Individual
Priority date: 1963-04-09
Filing date: 1963-04-09
Publication date: 1965-02-23
Anticipated expiration: 1982-02-23

Description

Feb. 23, 1965 HUGH L. DRYDEN 3,170,295

DEPUTY ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION PROPELLANT TANK PRESSURIZATION SYSTEM Filed April 9, 1963 FUEL m4 OXIDIZER 6 MARSHALL A. APPEL. DONQLD F1 1415/ TZEL IN V EN TORS ATTORNE-VS This system also has disadvantages.

United St 3,170,295 PROPELLANT TANK PRESSURIZATION SYSTEM Hugh L. Dryden, Deputy Administrator or the National Aeronautics and Space Administration, with respect to an invention of Marshall A. Appel and Donald F.

.Weitzel Filed Apr. 9, 1963, Ser. No. 271,823

6 Claims. '(Cl. Gil-39.48)

tes Patent oxygen tank, vaporize it, and use it to pressurize both the oxygen and fuel tanks. Some of the vaporized oxygen is fed to the oxygen tank. The remainder of the vaporized oxygen is used to inflate a bag carried inthe fuel tank. As the vaporized oxygen inflates the bag, it forces fuel out of the fuel tank. p j t There are a number of disadvantages in the above systern. It is dangerous. Oxygen rnight escape from the inflatable bag into the fuel tank. hypergolic-will ignite on contact. Also, an inflatable bag is bulky, and takes up room in the fuel tank. V

Another approach to pressurizing propellant tanks, has been to use a separate gas generator to provide hot combustion gases. These gases are mixed with an inert gas to cool them, and they are, then fed to both the oxidizer and fuel tanks to pressurize them. g

i It is heavy. Fuel necessary for the gas generaton the inert gas, and the container for the inert gas, all add weight to the system. Further, since the same mixture is fed to the oxidizer and oxidizer and fuel. It is also necessary that the products do not contanminate the propellants. important where the propellants are hypergolic.

In this inventiomhot combustion products and vaporized oxidizer are used to individually pressurize the propellant tanks. The combustion products pressurize the fuel tank, and the vaporized oxidizer pressurizes' the oxidizer tank. Fuel and oxidizer are obtained from the propellant tanks and are combined in afuel-rich mixture.

They are then combusted to completely consume the oxidizer and form hot combustion products. The hot combustion products are ,then fed' to a heat exchanger.

This is also very Many propellants are Additional oxidi'zer is then bled'from. the oxidizer propellant tank and passed throughthe heat exchanger where i itis vaporized by the hot combustion products. The oxidizer-in turn, cools the hot combustion products ,to a

7 temperature that is compatible with the fuel to be pressurized. I p

' The vaporized oxidizer isthen fed back to the oxidizer propellant tank to pressurize it. And, the combustion products are fed to the fuel propellant tank to-pressurize this tank. "It isQtherfore, propellants themselves to' pressurize the propellant tanks,

thereby eliminating the need for extra pressurant containers and accompanyingequipment. I A

It is also an object ofthis invention to directly pressurize propellant tanks with products that are completely compatible with the contents or each individual tank and that can bejed directly to the tanks.

an object r this invention to usethe ice Other objectives and advantages will appear from the specification and claims taken in connection with the drawing wherein in the single figure there is illustrated the propellant tank pressurization system in one type of propulsion system.

A preferred embodiment of. the invention is shown in the figure. There is provided propulsion motor 2 and propellant tanks land 6 containing propellant for the motor. Propellant tank 4 contains fuel such as RP-l (kerosene-base fuel) or similar propellant. Propellant tank 6 contains oxidizer suchas liquid oxygenor similar propellant.

Generally, depending on conditions to .be encountered, either a .gravity flow or positive feed means are used to feed the propellant from the tanks to the propulsion motor; In the embodiment disclosed, a positive propellant feed means is illustrated.

The propellant feed means includes: ducts 8, 10 connected to

tanks

4 and 6;

valves

12, 14 in the ducts; propellant pumps 16, 18 to feed the propellant; and gas turbine 20 to operate the propellant pumps. bine 29 passes through duct 21 to thrust chamber 2.

To initially start the flow of propellant to the propulsion motor, it is necessary to first start the turbine operating so it will in turn operate the propellant pumps. To start the turbine initially, a combustor meansor gas generator 22 is used. The gas generator is made witha starting supply of a liquid or solid propellant (not shown).

The combustion products from the generator are "fed lants are fed to the gas generator in a fuel-rich mixture.

The reason for this will be explained below. It is pointedfuel tanks, it is necessary that it be compatible w th both sustains itself to of turbine 20. Also, a small quantity of oxidizer. is fed to heat transfer means 34 by means in the form of bleed duct 38 connected to duct 10.

In heat transfer means 34, the combustion gases are at a high temperature and contain excess heat. The heat.

transfer means is constructed so that the hot combustion gases will be cooled by the oxidizer,.to a temperature that is compatible with the fuel being pressurized, and

the overall system. The excess heat from the combustion gases in turn is used to vaporize the oxidizer and raise its temperature to enable it to be used as a pressur ant gas.

Heat transfer means 34 is constructed so the hot com-.

bustion gases. from duct 36 pass'through tubing "40- The relatively cold oxidizer is circulated on the outside 42" of tubing 40. This is done so the oxidizer will act as" a shield to protect contiguous parts of the'system from the heat of the combustion gases.

The vaporized oxidizer and cooled combustion products A 1 are then fed from the heat transfer means to their

re spective tanks

4, 6. The vaporized oxidizer is fed .by' means in the form of duct 44 to tank 6. The cooled comv bustion. products are fed by means intheform of duct 46 to itsrespective tank 4. To control the flow of the pro- The output of tur generator 22 through

ducts

26, 28

pellants, each

duct

44, 46 contains a check valve 48, adjustable orifice valve 50 and relief valve 52.

A fuel-rich mixture is used in gas generator 22 to insure that the oxidizer will be completely consumed in the combustion process. This is to eliminate any danger of oxidizer being fed to the fuel propellant tank with the combustion products and contaminating the fuel. Also, as mentioned previously, if the propellants are hypergolic, the fuel would ignite on contact with any unconsumed oxidizer. The desired ratio of oxidizer to fuel feed can be obtained by adjusting valves 3t) and 32 in

ducts

26, 28.

The system does not require separate tanks or storage of pressurant gas.

Operation To initially start turbine 20 operating, gas may be generated in gas generator 22 by either a solid fuel (not shown) or from propellant (not shown) first obtained from the

propellant tanks

4, 6.

The high temperature, high pressure combustion products from gas generator 22, then flow through duct 24 to gas turbine 20 which operates propellant pumps 16, 18. Simultaneously, propellant pumps 16, 18 start to build up pressure. As pressure increases,

propellant valves

12, 14 open to feed fuel and oxidizer through ducts 8, it) into thrust chamber 2.

In a boot strap type of operation, fuel and oxidizer are then fed to gas generator 22 from

propellant tanks

4, 6; through conduits 8, 10; propellant pumps 16, 18;

conduits

26, 28; and valves 32, 36. The propellants are combusted in gas generator 22 at high temperature and pressure and hot combustion products fed through duct 24 to turbine 20.

The pressurants are fed to heat transfer means 34 from bleed ducts 36, 38. Bleed duct 36 is connected to hot gas duct 24 just up stream of the turbine 20 and directs a flow of a small quantity of hot gases to heat transfer means 34, and bleed duct 38 is connected in feed line 10 to feed oxidizer to be vaporized to heat transfer means 34.

As oxidizer passes through heat transfer means 34 it adsorbs heat from the hot combustion gases and is vaporized. The oxidizers temperature is raised to the degree required for use. The temperature of the hot gases is in turn lowered to a usable temperature. I

After passing through heat transfer means 34, the pressurants pass through their

respective ducts

44, 46, check valves 48, valves 50 that are made adjustable to provide a variable restriction in the line, and then into their respective tanks 4. 6. Relief valves 52 are adjusted to maintain a selected pressure in the system.

The following is an example of some of the temperatures that may be encountered in a system using RP-l as fuel, and liquid oxygen as an oxidizer. The temperature of the hot combustion gases in duct 24 going into the heat exchanger would be about 1700 F. The temperature of the liquid oxygen in duct 38 going into the heat exchanger would be around 292 F. Leaving the heat exchanger,- both pressurization gases will beat approximately +575 F.

The specific design of the heat exchanger is dependent upon a number of factors. For example, the propellants used, and exit temperatures of the pressurants required.

If the heat available in the combustion gases is higher than required to pressurize the fuel tank, additional cooling of the combustion gases may be attempted through a second heat exchanger inthe oxidizer feed line 38, or even in the oxidizer tank itself;

Conversely, when required, additional heating of the vaporized oxidizer may be obtained. A second heat exchanger may be placed in duct 21 leading from turbine 20 to thrust chamber 2; or through the use of additional hot gases obtained directly from thrust chamber 2.

Although but a single embodiment out of the present invention has been illustrated and described, it will be apparent to one skilled in the art that various changes and modifications may be made therein without departing from the invention as defined in the appended claims.

What is claimed is:

1. In a propulsion system a method of pressurizing propellant tanks, wherein one of said tanks contains oxidizer and one of said tanks contains fuel, comprising the steps of:

providing a portion of oxidizer and a portion of fuel in a fuel-rich mixture from said propellant tanks; combusting said mixture to completely consume said oxidizer and produce hot combustion products; providing additional oxidizer from said oxidizer propellant tank; transferring heat from said hot combustion products to said additional oxidizer to vaporize said oxidizer and lower the temperature of said combustion products;

feeding said vaporized oxidizer back to said oxidizer propellant tank to increase the pressure in said tank; and

feeding said relatively cooled combustion products to said fuel propellant tank to increase the pressure in said tank. 2. In a propulsion system a method of pressurizing propellant tanks wherein one of said tanks contains oxidizer and one of said tanks contains fuel, comprising the steps of:

providing a portion of oxidizer and a portion of fuel in a fuel-rich mixture from said propellant tanks;

combusting said mixture to completely consume said oxidizer and produce hot combustion products;

providing additional oxidizer from said oxidizer propellant tank;

surrounding said hot combustion products with said additional oxidizer propellant to act as a heat shield and to also transfer heat from said hot combustion products to said additional oxidizer to vaporize said additional oxidizer and lower the temperature of said combustion products; feeding said vaporized oxidizer back to said oxidizer propellant tank to increase the pressure in said tank;

and

feeding said relatively cooled combustion products to said fuel propellant tank to increase the pressure in said tank.

3. In a propulsion system, a construction for pressurizing propellant tanks, wherein one of said tanks contains oxidizer and one of said tanks contains fuel, the combina-- of fuel in a fuel-rich mixture from said propellanttanks; means to combust said mixture to completely consume said oxidizer and produce hot combustion products; means to provide additional oxidizer from said oxidizer propellant tank; heat transfer means to transfer heat from said hot combustion products to said additional oxidizer to vaporize said oxidizer and lower the temperature of said combustion products; 7 means to feed said vaporized oxidizer from said heat transfer means back to said oxidizer propellant tank to increase the pressure in said tank; and means to feed said relatively'cooled combustion products from said heat transfer means to said fuel propellanttank to increase the pressure in said tank. 4. In a propulsion system a construction for pressurizing propellant tanks, wherein one of said tanks contains oxidizer and one of said tanks contains fuel, the combination comprising: r

a gas generator; means to bleed .a portion of oxidizer and a portion of fuel in a fuel-rich mixture from said propellant tanks to said gas generator, said gas generator combusting said mixture to completely consume said means to feed said vaporized oxidizer to said oxidizer propellant tank-to increase the pressure in said tank; and

means to feed said relatively cooled combustion prodnets to said fuel propellant tank to increase the pressure in said tank. v 5.] In a propulsion system a construction for pressurizing propellant tanks wherein one of said tankscontains v fuel and one of said tanks contains oxidizer, the combination comprising: 1

first and second propellant pumps;

. 6 r to said turbine to feed combustion products from said gas generator to said turbine; heat transfer means;

,' bleed duct means to feed oxidizer from said first propellant pump to said heat'transfer means;

bleed duct means upstream of said turbine to feed hot combustion products from said gas generator to said heat transfer means; a

means to adjust the feeds of said oxidizer and hot combustion products to said heat transfer means in an amount sufiicient to vaporize said oxidizer and lower the temperature of said hot combustion products;

duct means to feed vaporized oxidizer from said heat transfer means to said oxidizer propellant tank to in- V crease the presesure in said tank; and

.duct means to feed said combustion products from said heat transfer means to' said fuel tank to increase the pressure in said fuel tank. 7

6. A device as set forth in claim 5 wherein said heat duct means connecting. said oxidizer tank to the inlet 20 transfer means is a heat exchanger, and said heat exchangof said first propellant pump; p duct means connecting said fuel tank to the inlet of said second propellant pump; a turbine connected to drive said propellant pumps; a gas generator;

7 individual duct means connecting the outlet-sot vsaid first and second propellant pumps to the inlet of said gas generator; valve means to adjust the feeds of said oxidizer and said fuel to said gas generator to provide afuel-rich mixture; I I ductmeans connecting the outlet of said gas generator er is constructed with tubing through which the hot combustion products pass, and the oxidizer is circulated on the outside of said tubing to act as a heat shield.

SAMUEL LEVINE, Primary Examiner.

Claims

5. IN A PROPULSION SYSTEM A CONSTRUCTION FOR PRESSURIZING PROPELLANT TANKS WHEREIN ONE OF SAID TANKS CONTAINS FUEL AND ONE OF SAID TANKS CONTAINS OXIDIZER, THE COMBINATION COMPRISING: FIRST AND SECOND PROPELLANT PUMPS; DUCT MEANS CONNECTING SAID OXIDIZER TANK TO THE INLET OF SAID FIRST PROPELLANT PUMP; DUCT MEANS CONNECTING SAID FUEL TANK TO THE INLET OF SAID SECOND PROPELLANT PUMP; A TURBINE CONNECTED TO DRIVE SAID PROPELLANT PUMPS; A GAS GENERATOR; INDIVIDUAL DUCT MEANS CONNECTING THE OUTLETS OF SAID FIRST AND SECOND PROPELLANT PUMPS TO THE INLET OF SAID GAS GENERATOR; VALVE MEANS TO ADJUST THE FEEDS OF SAID OXIDIZER AND SAID FUEL TO SAID GAS GENERATOR TO PROVIDE A FUEL-RICH MIXTURE; DUCT MEANS CONNECTING THE OUTLET OF SAID GAS GENERATOR TO SAID TURBINE TO FEED COMBUSTION PRODUCTS FROM SAID GAS GENERATOR TO SAID TURBINE; HEAT TRANSFER MEANS; BLEED DUCT MEANS TO FEED OXIDIZER FROM SAID FIRST PROPELLANT PUMP TO SAID HEAT TRANSFER MEANS; BLEED DUCT MEANS UPSTREAM OF SAID TURBINE TO FEED HOT COMBUSTION PRODUCTS FROM SAID GAS GENERATOR TO SAID HEAT TRANSFER MEANS; MEANS TO ADJUST THE FEEDS OF SAID OXIDIZER AND HOT COMBUSTION PRODUCTS TO SAID HEAT TRANSFER MEANS IN AN AMOUNT SUFFICIENT TO VAPORIZE SAID OXIDIZER AND LOWER THE TEMPERATURE OF SAID HOT COMBUSTION PRODUCTS; DUCT MEANS TO FEED VAPORIZED OXIDIZER FROM SAID HEAT TRANSFER MEANS TO SAID OXIDIZER PROPELLANT TANK TO INCREASE THE PRESSURE IN SAID TANK; AND DUCT MEANS TO FEED SAID COMBUSTION PRODUCTS FROM SAID HEAT TRANSFER MEAND TO SAID FUEL TANK TO INCREASE THE PRESSURE IN SAID FUEL TANK.