US3793861A - Transpiration cooling structure - Google Patents

Transpiration cooling structure Download PDF

Info

Publication number
US3793861A
US3793861A US00231619A US3793861DA US3793861A US 3793861 A US3793861 A US 3793861A US 00231619 A US00231619 A US 00231619A US 3793861D A US3793861D A US 3793861DA US 3793861 A US3793861 A US 3793861A
Authority
US
United States
Prior art keywords
coolant
cooling structure
transpiration cooling
temperature
permeability
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 - Lifetime
Application number
US00231619A
Inventor
K Burkhard
T Lee
J Schuster
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
McDonnell Douglas Corp
Original Assignee
McDonnell Douglas Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by McDonnell Douglas Corp filed Critical McDonnell Douglas Corp
Application granted granted Critical
Publication of US3793861A publication Critical patent/US3793861A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/52—Protection, safety or emergency devices; Survival aids
    • B64G1/58—Thermal protection, e.g. heat shields
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles

Definitions

  • ABSTRACT A high surface temperature transpiration cooling structure that substantially reduces coolant requirements is described It is a dual layer material consisting of a thin outer overlay of a high melting temperature, low thermal conductivity, porous ceramic material of high permeability applied on a thicker sintered metallic substrate of a high strength material of low permeability. A coolant is expelled through this structure and out the heated surface to keep the surface temperature below the overlay melting point.
  • the inner layer controls coolant distribution and the outer layer buffers the inner layer without creating a high back pressure. This structure may be used whenever it may be subjected to a high heating environment.
  • transpiration cooling uses a porous material of a single permeability, or passibility.
  • the fluid coolant must be kept at a temperature below its boiling point within the material. This is because when high surface temperature operation is attempted, coolant tends to divert around regions in which boiling is occurring, allowing hot spots to form. The development and propagation of these hot spots eventually leads to a failure because the transpiration cooled surface melts in those areas where coolant flow has been reduced.
  • hot spots may form regardless of whether the coolant is initially supplied in the liquid or vapor phase. This is because once the coolant is in the vapor phase, its resistance to flow through porous material increases with increasing porous material temperature.
  • Another existing system allows internal boiling of the liquid without the formation of hot spots, but is of a single metallic material throughout. This limits the surface temperature to the melting temperature of the metal which in the case of stainless steel is approximately 2300 Fahrenheit. Because of this relatively low temperature, a relatively large amount of coolant is needed.
  • Transpiration cooling efficiency can be increased by operating at high surface temperature. For a liquid coolant this implies coolant phase change to vapor within the porous material. Whether the coolant is initially a liquid or gas, operational instability can result at high temperature due tothe relationships between coolant viscosity and temperature and coolant density and temperature. This instability problem is avoided, in accordance with the present invention, by the provision of a dual permeability porous structure having an inner layer of material controlling coolant flow and an outer layer buffering the inner layer from high environmental temperature without creating a high back pressure.
  • the inner layer is a high strength metallic material such as porous sintered stainless steel, and has a relatively low permeability in order to control the coolant flow through the dual layered structure.
  • the outer layer is a high melting temperature, low thermal conductivity, porous ceramic material such as zirconia with a relatively high permeability compared with the inner layer so as to buffer the inner layer from high temperature (beyond its melting point) and yet not develop a high back pressure.
  • a high back pressure could have an adverse effect on coolant flow distribution thus affecting operational stability.
  • the coolant flow rate can be reduced below what would be required to operate with low surface temperature.
  • FIG. 1 is a sectional view of a missile nose tip embodiment
  • FIG. 2 is a graphic illustration of the material characteristics taken in section
  • FIG. 3 is a graphic illustration of the temperature distribution of this material.
  • FIG. 1 wherein there is shown a reentry nose tip 10 comprising a wand 12 having a fluid conductive path 14 therein for a coolant such as water.
  • An ablative heat shield 16 surrounds the wand.
  • the nose tip includes a low permeability, high strength substrate 18 such as sintered stainless steel coated on the outside with a high temperature, high permeability overlay 20 such as zirconia, for example.
  • Substrate 18 has a reservoir 22 to which a conduit 14 passes the cooling fluid.
  • the coolant first passes through the high strength inner matrix 18 where its low permeability meters the distribution of the coolant to the heated surface 20 and its high strength contains the pressure stresses.
  • the coolant then passes into the overlay region 20 where, in the case of liquid, it will boil and expand into a gas and, in the case of gas, will also expand due to the large temperature increase as it passes through this region. Because of the high permeability of the outer region 20, the density decrease of the coolant and viscosity increase of the coolant with temperature will not have a significant effect on the overall pressure drop between the substrate 18 and the heated surface 20 and therefore will not effect the distribution of flow out the heated surface. Since the distribution of coolant flow is not affected by surface temperature, hot spots will not form and propagate as they would without the surface layer.
  • the overlay 20 in one embodiment may be zirconia although other high temperature materials may be utilized.
  • Zirconia is a ceramic material used to line furnaces in brick or cement form but it is very difficult to fuse.
  • Application with a plasma gun is a satisfactory method in which an electric arc is struck between high temperature electrodes.
  • An inert gas such as argon or helium is passed around the electrodes in order to pick up the thermal energy to heat the gas.
  • the gas temperature is then hot enough to melt zirconia particles, the melting point of which is on the order of 4800F.
  • the gas stream continues out of the plasma gun with the zirconia powder injected into it and is sprayed onto the work surface.
  • the zirconia powder in the gas stream becomes plastic or putty-like and results in a mechanical attachment to the surface upon which it is sprayed.
  • the substrate 18 may be so shaped and thus adjust the coolant flow rate to keep the surface temperature of the outer layer 20 at a temperature below the melting point of the high temperature outer surface material.
  • the thin overlay 20 is of a high temperature, low conductivity, porous material of high permeability applied to the thicker substrate matrix 18 of high strength, high density, low permeability, high conductivity material.
  • the purpose of the overlay of material 20 is to act as a buffer region to shield the high strength substrate 18 from the elevated temperature caused by heating shown by arrows 24. Because of its low conductivity, a very large temperature differential can be maintained across the overlay during the Operation. Due to the permeability differential between the overlay 20 and substrate material 18, the substrate 18 will have a dominating effect on metering the distribution of coolant 26 out through the heated surface 20, thus avoiding hot spots and subsequent surface melting that could occur without the overlay 20.
  • the coolant temperature in the substrate 18 and through most of the outer surface layer 20 remains fairly constant and substantially below the coolant boiling temperature. However, near the outer surface the coolant boils or changes phase and a high temperature gradient is developed, permitting a high surface temperature. This high surface temperature results in less heat being transferred into the surface, therefore requiring less coolant. Additionally, since the coolant exits from the surface at approximately the surface temperature, higher surface temperature results in a greater amount of energy being absorbed per unit weight of coolant. Therefore, less coolant is required to absorb a given amount of heat being conducted from the outside into the surface.
  • a high surface temperature transpiration cooling structure comprising a dual permeability material for a coolant passing therethrough
  • said material consisting of an outer portion of high melting temperature, low thermal conductivity, porous material of relatively high permeability, and a high strength inner portion of relatively lower permeability.

Abstract

A high surface temperature transpiration cooling structure that substantially reduces coolant requirements is described. It is a dual layer material consisting of a thin outer overlay of a high melting temperature, low thermal conductivity, porous ceramic material of high permeability applied on a thicker sintered metallic substrate of a high strength material of low permeability. A coolant is expelled through this structure and out the heated surface to keep the surface temperature below the overlay melting point. The inner layer controls coolant distribution and the outer layer buffers the inner layer without creating a high back pressure. This structure may be used whenever it may be subjected to a high heating environment.

Description

United States Patent [1 1 Burkhard et a1.
[ TRANSPIRATION COOLING STRUCTURE [75] Inventors: Kurt Burkhard, Irvine; Thomas G.
Lee, Anaheim; John R. Schuster, Fountain Valley, all of Calif.
[73] Assignee: McDonnell Douglas Corporation,
Santa Monica, Calif.
[22] Filed: Mar. 3, 1972 [21] App]. No.: 231,619
[56] References Cited UNITED STATES PATENTS 2,908,455 10/1959 Hoadley 62/315 2,941,759
6/1960 Rice 3/1963 Alvis Feb. 26, 1974 3,138,009 6/1964 MCCreight 62/315 Primary ExaminerWi1liam J. Wye Attorney, Agent, or FirmRobert O. Richardson; Walter J. Jason; Donald L. Royer [57] ABSTRACT A high surface temperature transpiration cooling structure that substantially reduces coolant requirements is described It is a dual layer material consisting of a thin outer overlay of a high melting temperature, low thermal conductivity, porous ceramic material of high permeability applied on a thicker sintered metallic substrate of a high strength material of low permeability. A coolant is expelled through this structure and out the heated surface to keep the surface temperature below the overlay melting point. The inner layer controls coolant distribution and the outer layer buffers the inner layer without creating a high back pressure. This structure may be used whenever it may be subjected to a high heating environment.
6 Claims, 3 Drawing Figures TRANSPIRATION COOLING STRUCTURE BACKGROUND OF THE PRESENT INVENTION Transpiration is the act of excreting a liquid, vapor, or gas through a surface as a means of cooling the surface. This type of thermal protection is particularly desirable in a high heat environment such as experienced by nose cones for reentry vehicles, missile leading edges and nose tips, rocket nozzles and combustion chamber linings, steam and gas turbine blades, and instruments exposed to a high heat flux.
One existing concept of transpiration cooling uses a porous material of a single permeability, or passibility. With this system the fluid coolant must be kept at a temperature below its boiling point within the material. This is because when high surface temperature operation is attempted, coolant tends to divert around regions in which boiling is occurring, allowing hot spots to form. The development and propagation of these hot spots eventually leads to a failure because the transpiration cooled surface melts in those areas where coolant flow has been reduced. With this concept, hot spots may form regardless of whether the coolant is initially supplied in the liquid or vapor phase. This is because once the coolant is in the vapor phase, its resistance to flow through porous material increases with increasing porous material temperature.
Another existing system allows internal boiling of the liquid without the formation of hot spots, but is of a single metallic material throughout. This limits the surface temperature to the melting temperature of the metal which in the case of stainless steel is approximately 2300 Fahrenheit. Because of this relatively low temperature, a relatively large amount of coolant is needed.
SUMMARY OF PRESENT INVENTION Transpiration cooling efficiency can be increased by operating at high surface temperature. For a liquid coolant this implies coolant phase change to vapor within the porous material. Whether the coolant is initially a liquid or gas, operational instability can result at high temperature due tothe relationships between coolant viscosity and temperature and coolant density and temperature. This instability problem is avoided, in accordance with the present invention, by the provision of a dual permeability porous structure having an inner layer of material controlling coolant flow and an outer layer buffering the inner layer from high environmental temperature without creating a high back pressure.
The inner layer is a high strength metallic material such as porous sintered stainless steel, and has a relatively low permeability in order to control the coolant flow through the dual layered structure. The outer layer is a high melting temperature, low thermal conductivity, porous ceramic material such as zirconia with a relatively high permeability compared with the inner layer so as to buffer the inner layer from high temperature (beyond its melting point) and yet not develop a high back pressure. A high back pressure could have an adverse effect on coolant flow distribution thus affecting operational stability. As this design concept permits stable operation with high surface temperature, the coolant flow rate can be reduced below what would be required to operate with low surface temperature.
BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a sectional view of a missile nose tip embodiment;
FIG. 2 is a graphic illustration of the material characteristics taken in section; and
FIG. 3 is a graphic illustration of the temperature distribution of this material.
DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENT Reference is now made to FIG. 1 wherein there is shown a reentry nose tip 10 comprising a wand 12 having a fluid conductive path 14 therein for a coolant such as water. An ablative heat shield 16 surrounds the wand. The nose tip includes a low permeability, high strength substrate 18 such as sintered stainless steel coated on the outside with a high temperature, high permeability overlay 20 such as zirconia, for example. Substrate 18 has a reservoir 22 to which a conduit 14 passes the cooling fluid. The coolant first passes through the high strength inner matrix 18 where its low permeability meters the distribution of the coolant to the heated surface 20 and its high strength contains the pressure stresses. The coolant then passes into the overlay region 20 where, in the case of liquid, it will boil and expand into a gas and, in the case of gas, will also expand due to the large temperature increase as it passes through this region. Because of the high permeability of the outer region 20, the density decrease of the coolant and viscosity increase of the coolant with temperature will not have a significant effect on the overall pressure drop between the substrate 18 and the heated surface 20 and therefore will not effect the distribution of flow out the heated surface. Since the distribution of coolant flow is not affected by surface temperature, hot spots will not form and propagate as they would without the surface layer.
The overlay 20 in one embodiment may be zirconia although other high temperature materials may be utilized. Zirconia is a ceramic material used to line furnaces in brick or cement form but it is very difficult to fuse. Application with a plasma gun is a satisfactory method in which an electric arc is struck between high temperature electrodes. An inert gas such as argon or helium is passed around the electrodes in order to pick up the thermal energy to heat the gas. The gas temperature is then hot enough to melt zirconia particles, the melting point of which is on the order of 4800F. The gas stream continues out of the plasma gun with the zirconia powder injected into it and is sprayed onto the work surface. The zirconia powder in the gas stream becomes plastic or putty-like and results in a mechanical attachment to the surface upon which it is sprayed. The substrate 18 may be so shaped and thus adjust the coolant flow rate to keep the surface temperature of the outer layer 20 at a temperature below the melting point of the high temperature outer surface material.
As shown in FIG. 2, the thin overlay 20 is of a high temperature, low conductivity, porous material of high permeability applied to the thicker substrate matrix 18 of high strength, high density, low permeability, high conductivity material. The purpose of the overlay of material 20 is to act as a buffer region to shield the high strength substrate 18 from the elevated temperature caused by heating shown by arrows 24. Because of its low conductivity, a very large temperature differential can be maintained across the overlay during the Operation. Due to the permeability differential between the overlay 20 and substrate material 18, the substrate 18 will have a dominating effect on metering the distribution of coolant 26 out through the heated surface 20, thus avoiding hot spots and subsequent surface melting that could occur without the overlay 20.
As shown in FIG. 3, the coolant temperature in the substrate 18 and through most of the outer surface layer 20 remains fairly constant and substantially below the coolant boiling temperature. However, near the outer surface the coolant boils or changes phase and a high temperature gradient is developed, permitting a high surface temperature. This high surface temperature results in less heat being transferred into the surface, therefore requiring less coolant. Additionally, since the coolant exits from the surface at approximately the surface temperature, higher surface temperature results in a greater amount of energy being absorbed per unit weight of coolant. Therefore, less coolant is required to absorb a given amount of heat being conducted from the outside into the surface.
Having thus described an illustrative embodiment of the present invention, it is to be understood that modifications thereof will become apparent to those skilled in the art and it is to be understood that these deviations are to be construed as part of the present invention.
We claim:
1. A high surface temperature transpiration cooling structure comprising a dual permeability material for a coolant passing therethrough,
said material consisting of an outer portion of high melting temperature, low thermal conductivity, porous material of relatively high permeability, and a high strength inner portion of relatively lower permeability.
2. A transpiration cooling structure as in claim 1 wherein said outer portion is an overlay of dissimilar material applied to said inner portion.
3. A transpiration cooling structure as in claim 1 in combination coolant means for expulsion through said material.
4. A transpiration cooling structure as in claim 3 wherein a major portion of coolant pressure drop occurs through said inner portion and coolant flows through said outer portion without a high back pressure.
5. A transpiration cooling structure as in claim 1 wherein said inner portion is a sintered metal, said outer portion is a porous ceramic, and said coolant is a liquid.
6. A transpiration cooling structure as in claim 5 wherein said metal is a sintered stainless steel, said ceramic is zirconia, and said liquid is water.

Claims (6)

1. A high surface temperature transpiration cooling structure comprising a dual permeability material for a coolant passing therethrough, said material consisting of an outer portion of high melting temperature, low thermal conductivity, porous material of relatively high permeability, and a high strength inner portion of relatively lower permeability.
2. A transpiration cooling structure as in claim 1 wherein said outer portion is an overlay of dissimilar material applied to said inner portion.
3. A transpiration cooling structure as in claim 1 in combination coolant means for expulsion through said material.
4. A transpiration cooling structure as in claim 3 wherein a major portion of coolant pressure drop occurs through said inner portion and coolant flows through said outer portion without a high back pressure.
5. A transpiration cooling structure as in claim 1 wherein said inner portion is a sintered metal, said outer portion is a porous ceramic, and said coolant is a liquid.
6. A transpiration cooling structure as in claim 5 wherein said metal is a sintered stainless steel, said ceramic is zirconia, and said liquid is water.
US00231619A 1972-03-03 1972-03-03 Transpiration cooling structure Expired - Lifetime US3793861A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US23161972A 1972-03-03 1972-03-03

Publications (1)

Publication Number Publication Date
US3793861A true US3793861A (en) 1974-02-26

Family

ID=22869992

Family Applications (1)

Application Number Title Priority Date Filing Date
US00231619A Expired - Lifetime US3793861A (en) 1972-03-03 1972-03-03 Transpiration cooling structure

Country Status (1)

Country Link
US (1) US3793861A (en)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3883096A (en) * 1974-03-12 1975-05-13 Us Army Transpiration cooled nose cone
FR2542698A1 (en) * 1983-03-18 1984-09-21 Erno Raumfahrttechnik Gmbh Heat shield for ultrasonic aircraft
FR2547895A1 (en) * 1983-06-27 1984-12-28 Aerospatiale COMPOSITE ASSEMBLY FORMING SCREEN FOR PROTECTION OR THERMAL DISSIPATION
EP0136071A1 (en) * 1983-08-26 1985-04-03 Westinghouse Electric Corporation Varying thickness thermal barrier for combustion turbine baskets
US4557444A (en) * 1984-01-09 1985-12-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Aerospace vehicle
US4991797A (en) * 1989-01-17 1991-02-12 Northrop Corporation Infrared signature reduction of aerodynamic surfaces
US5139716A (en) * 1990-02-20 1992-08-18 Loral Aerospace Corp. Method of fabricating coolable ceramic structures
GB2267733A (en) * 1992-05-13 1993-12-15 Gen Electric Abrasion protective and thermal dissipative coating for jet engine component leading edges.
US5330124A (en) * 1992-03-03 1994-07-19 Aerospatiale Societe Nationale Industrielle Thermal protection device using the vaporization and superheating of a rechargeable liquid
DE3931976C2 (en) * 1988-09-26 2001-08-16 Rockwell International Corp Integral structure and thermal protection system
US6375425B1 (en) 2000-11-06 2002-04-23 General Electric Company Transpiration cooling in thermal barrier coating
US20040245373A1 (en) * 2003-06-09 2004-12-09 Behrens William W. Actively cooled ceramic thermal protection system
US20060242907A1 (en) * 2005-04-29 2006-11-02 Sprouse Kenneth M Gasifier injector
US20070012820A1 (en) * 2004-08-11 2007-01-18 David Buehler Reusable upper stage
US20070012821A1 (en) * 2004-08-11 2007-01-18 Buehler David B Launch vehicle crew escape system
US20100300063A1 (en) * 2009-02-26 2010-12-02 Palmer Labs, LLC. Apparatus and Method for Combusting a Fuel at High Pressure and High Temperature, and Associated System and Device
US20110083435A1 (en) * 2009-02-26 2011-04-14 Palmer Labs, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
EP2519725A2 (en) * 2009-12-29 2012-11-07 Rolls-Royce Corporation Gas turbine engine component construction
JP2013121786A (en) * 2011-12-12 2013-06-20 Kawasaki Heavy Ind Ltd Ablator
US8869889B2 (en) 2010-09-21 2014-10-28 Palmer Labs, Llc Method of using carbon dioxide in recovery of formation deposits
US8986002B2 (en) 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US10859264B2 (en) 2017-03-07 2020-12-08 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11199327B2 (en) 2017-03-07 2021-12-14 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
US11572828B2 (en) 2018-07-23 2023-02-07 8 Rivers Capital, Llc Systems and methods for power generation with flameless combustion

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2908455A (en) * 1957-04-11 1959-10-13 United Aircraft Corp Surface cooling means for aircraft
US2941759A (en) * 1957-01-14 1960-06-21 Gen Dynamics Corp Heat exchanger construction
US3082611A (en) * 1960-07-08 1963-03-26 Ling Temco Vought Inc Protective means
US3138009A (en) * 1957-04-17 1964-06-23 Gen Electric Transpiration cooling system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2941759A (en) * 1957-01-14 1960-06-21 Gen Dynamics Corp Heat exchanger construction
US2908455A (en) * 1957-04-11 1959-10-13 United Aircraft Corp Surface cooling means for aircraft
US3138009A (en) * 1957-04-17 1964-06-23 Gen Electric Transpiration cooling system
US3082611A (en) * 1960-07-08 1963-03-26 Ling Temco Vought Inc Protective means

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3883096A (en) * 1974-03-12 1975-05-13 Us Army Transpiration cooled nose cone
FR2542698A1 (en) * 1983-03-18 1984-09-21 Erno Raumfahrttechnik Gmbh Heat shield for ultrasonic aircraft
EP0133066A3 (en) * 1983-06-27 1986-03-05 Societe Nationale Industrielle Aerospatiale Laminate for thermal protection or heat dispersion means
EP0133066A2 (en) * 1983-06-27 1985-02-13 Aerospatiale Societe Nationale Industrielle Laminate for thermal protection or heat dispersion means
FR2547895A1 (en) * 1983-06-27 1984-12-28 Aerospatiale COMPOSITE ASSEMBLY FORMING SCREEN FOR PROTECTION OR THERMAL DISSIPATION
US4592950A (en) * 1983-06-27 1986-06-03 Societe Nationale Industrielle Et Aerospatiale Composite assembly forming thermal protection or dissipation screen
EP0136071A1 (en) * 1983-08-26 1985-04-03 Westinghouse Electric Corporation Varying thickness thermal barrier for combustion turbine baskets
US4557444A (en) * 1984-01-09 1985-12-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Aerospace vehicle
DE3931976C2 (en) * 1988-09-26 2001-08-16 Rockwell International Corp Integral structure and thermal protection system
US4991797A (en) * 1989-01-17 1991-02-12 Northrop Corporation Infrared signature reduction of aerodynamic surfaces
US5139716A (en) * 1990-02-20 1992-08-18 Loral Aerospace Corp. Method of fabricating coolable ceramic structures
US5330124A (en) * 1992-03-03 1994-07-19 Aerospatiale Societe Nationale Industrielle Thermal protection device using the vaporization and superheating of a rechargeable liquid
GB2267733A (en) * 1992-05-13 1993-12-15 Gen Electric Abrasion protective and thermal dissipative coating for jet engine component leading edges.
US6375425B1 (en) 2000-11-06 2002-04-23 General Electric Company Transpiration cooling in thermal barrier coating
US7275720B2 (en) * 2003-06-09 2007-10-02 The Boeing Company Actively cooled ceramic thermal protection system
US20040245373A1 (en) * 2003-06-09 2004-12-09 Behrens William W. Actively cooled ceramic thermal protection system
US20070012820A1 (en) * 2004-08-11 2007-01-18 David Buehler Reusable upper stage
US20070012821A1 (en) * 2004-08-11 2007-01-18 Buehler David B Launch vehicle crew escape system
US8196848B2 (en) * 2005-04-29 2012-06-12 Pratt & Whitney Rocketdyne, Inc. Gasifier injector
US20060242907A1 (en) * 2005-04-29 2006-11-02 Sprouse Kenneth M Gasifier injector
US8308829B1 (en) 2005-04-29 2012-11-13 Pratt & Whitney Rocketdyne, Inc. Gasifier injector
US9416728B2 (en) 2009-02-26 2016-08-16 8 Rivers Capital, Llc Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device
US20110083435A1 (en) * 2009-02-26 2011-04-14 Palmer Labs, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US20100300063A1 (en) * 2009-02-26 2010-12-02 Palmer Labs, LLC. Apparatus and Method for Combusting a Fuel at High Pressure and High Temperature, and Associated System and Device
US8986002B2 (en) 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9068743B2 (en) 2009-02-26 2015-06-30 8 Rivers Capital, LLC & Palmer Labs, LLC Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9341118B2 (en) 2009-12-29 2016-05-17 Rolls-Royce Corporation Various layered gas turbine engine component constructions
EP2519725A2 (en) * 2009-12-29 2012-11-07 Rolls-Royce Corporation Gas turbine engine component construction
EP2519725A4 (en) * 2009-12-29 2015-03-25 Rolls Royce Corp Gas turbine engine component construction
US8869889B2 (en) 2010-09-21 2014-10-28 Palmer Labs, Llc Method of using carbon dioxide in recovery of formation deposits
JP2013121786A (en) * 2011-12-12 2013-06-20 Kawasaki Heavy Ind Ltd Ablator
US10859264B2 (en) 2017-03-07 2020-12-08 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11199327B2 (en) 2017-03-07 2021-12-14 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
US11435077B2 (en) 2017-03-07 2022-09-06 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11828468B2 (en) 2017-03-07 2023-11-28 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
US11572828B2 (en) 2018-07-23 2023-02-07 8 Rivers Capital, Llc Systems and methods for power generation with flameless combustion

Similar Documents

Publication Publication Date Title
US3793861A (en) Transpiration cooling structure
US3138009A (en) Transpiration cooling system
US3026806A (en) Ballistic missile nose cone
Huang et al. Experimental investigation of transpiration cooling with phase change for sintered porous plates
Al-Jothery et al. A review of ultra-high temperature materials for thermal protection system
US3069847A (en) Rocket wall construction
US3157026A (en) Composite nozzle structure
Li et al. Ablation behavior of sharp leading edge parts made of rare earth La-compound modified ZrB2 coated C/C composites
US4949920A (en) Ablative cooling of aerodynamically heated radomes
Li et al. Preparation and properties of TaSi2-MoSi2-ZrO2-borosilicate glass coating on porous SiCO ceramic composites for thermal protection
Ritt et al. Arc jet testing and evaluation of Mo–Si–B coated Mo and SiC–ZrB2 ceramics
Wong Solid rocket nozzle design summary
CA1076657A (en) Method and apparatus for projecting solids containing gaseous media into an arc discharge
US3493177A (en) Method of and means for cooling the throat wall of rocket engine nozzle
Lü et al. Numerical and experimental investigation of aerodynamic heat control of leading edge of hypersonic vehicle’s flexible skin
Reimer et al. Arc jet testing of CMC samples with transpiration cooling
US3177811A (en) Composite heat-resistant construction
Dwork Coning Effects Caused by Separation of Spin-Stabilized Stages
JP3341780B2 (en) Crucible for vacuum deposition equipment
US3265314A (en) Heat dispersing swivel rocket nozzle liner
US3050000A (en) Hypervelocity fluid flow temperature limiter
Schuster et al. Application of an improved transpiration cooling concept to space shuttle type vehicles
ETEMAD Oxidation and mechanical performance of tungsten at high temperatures and high pressures.
US3298175A (en) Method and device for cooling
CN107990769A (en) A kind of metal lightweight thermal protection system realized based on fuel oil cooling flat-plate heat pipe